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Relevant bibliographies by topics / Low pressure turbine blade design

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Academic literature on the topic 'Low pressure turbine blade design'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

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Journal articles on the topic "Low pressure turbine blade design"

1

Hu, Site, Chao Zhou, and Shiyi Chen. "Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences." International Journal of Turbo & Jet-Engines 37, no. 2 (September 25, 2020): 195–207. http://dx.doi.org/10.1515/tjj-2017-0020.

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AbstractIncreasing the blade loading of a low pressure turbine blade decreases the number of blades, thus improving the aero-engine performance in terms of the weight and manufacture cost. Many studies focused on the blade-to-blade flow field of ultra-high lift low pressure turbines. The secondary flows of ultra-high lift low pressure turbines received much less attention. This paper investigates the secondary flows in an ultra-high lift low pressure turbine cascade T106C by large eddy simulation at a Reynolds number of 100,000. Both time-averaged and instantaneous flow fields of this ultra-high lift low pressure turbine are presented. To understand the effects of the inlet angle, five incidences of ‒10°, ‒5°, 0, +5° and +10° are investigated. The case at the design incidence is analyzed first. Detailed data is used to illustrate the how the fluids in boundary layers develops into secondary flows. Then, the cases with different inlet incidences are discussed. The aerodynamic performances are compared. The effect of blade loading on the vortex structures is investigated. The horseshoe vortex, passage vortex and the suction side corner vortex are very sensitive to the loading of the front part of the blade.

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2

Curtis, E. M., H. P. Hodson, M. R. Banieghbal, J. D. Denton, R. J. Howell, and N. W. Harvey. "Development of Blade Profiles for Low-Pressure Turbine Applications." Journal of Turbomachinery 119, no. 3 (July 1, 1997): 531–38. http://dx.doi.org/10.1115/1.2841154.

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This paper describes a program of work, largely experimental, which was undertaken with the objective of developing an improved blade profile for the low-pressure turbine in aero-engine applications. Preliminary experiments were conducted using a novel technique. An existing cascade of datum blades was modified to enable the pressure distribution on the suction surface of one of the blades to be altered. Various means, such as shaped inserts, an adjustable flap at the trailing edge, and changing stagger were employed to change the geometry of the passage. These experiments provided boundary layer and lift data for a wide range of suction surface pressure distributions. The data were then used as a guide for the development of new blade profiles. The new blade profiles were then investigated in a low-speed cascade that included a set of moving bars upstream of the cascade of blades to simulate the effect of the incoming wakes from the previous blade row in a multistage turbine environment. Results are presented for two improved profiles that are compared with a datum representative of current practice. The experimental results include loss measurements by wake traverse, surface pressure distributions, and boundary layer measurements. The cascades were operated over a Reynolds number range from 0.7 × 105 to 4.0 × 105. The first profile is a “laminar flow” design that was intended to improve the efficiency at the same loading as the datum. The other is a more highly loaded blade profile intended to permit a reduction in blade numbers. The more highly loaded profile is the most promising candidate for inclusion in future designs. It enables blade numbers to be reduced by 20 percent, without incurring any efficiency penalty. The results also indicate that unsteady effects must be taken into consideration when selecting a blade profile for the low-pressure turbine.

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3

Panovsky, J., and R. E. Kielb. "A Design Method to Prevent Low Pressure Turbine Blade Flutter." Journal of Engineering for Gas Turbines and Power 122, no. 1 (October 20, 1999): 89–98. http://dx.doi.org/10.1115/1.483180.

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A design approach to avoid flutter of low pressure turbine blades in aircraft engines is described. A linearized Euler analysis, previously validated using experimental data, is used for a series of parameter studies. The influence of mode shape and reduced frequency are investigated. Mode shape is identified as the most important contributor to determining the stability of a blade design. A new stability parameter is introduced to gain additional insight into the key contributors to flutter. This stability parameter is derived from the influence coefficient representation of the cascade, and includes only contributions from the reference blade and its immediate neighbors. This has the effect of retaining the most important contributions to aerodynamic damping while filtering out terms of less significance. This parameter is utilized to develop a stability map, which provides the critical reduced frequency as a function of torsion axis location. Rules for preliminary design and procedures for detailed design analysis are defined. [S0742-4795(00)01401-0]

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4

Jiang, Chuhua, Xuedao Shu, Junhua Chen, Lingjie Bao, and Yawen Xu. "Research on Blade Design of Lift–Drag-Composite Tidal-Energy Turbine at Low Flow Velocity." Energies 14, no. 14 (July 14, 2021): 4258. http://dx.doi.org/10.3390/en14144258.

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The research on tidal-current energy-capture technology mainly focuses on the conditions of high flow velocity, focusing on the use of differential pressure lift, while the average flow velocity in most sea areas of China is less than 1.5 m/s, especially in the marine aquaculture area, where tidal-current energy is needed to provide green energy locally. Due to the low flow velocity of this type of sea area, it seriously affects the effect of differential pressure lift, which is conducive to exerting the effect of impact resistance. In this regard, the coupling effect of the differential pressure lift and the impact resistance on the blade torque is comprehensively considered, this research puts forward the design method of the lift-–drag-composite thin-plate arc turbine blade. Based on the blade element momentum (BEM) theory and Bernoulli’s principle, the turbine dynamic model was established, and the nonlinear optimization method was used to solve the shape parameters of the turbine blades, and the thin-plate arc and NACA airfoil blade turbines were trial-produced under the same conditions. A model experiment was carried out in the experimental pool, and the Xiangshan sea area in Ningbo, East China Sea was taken as the experimental sea area. The results of the two experiments showed the same trend, indicating that the energy-harvesting performance of the lift–drag-composite blade was significantly better than that of the lift blade under the conditions of low flow velocity and small radius, which verified the correctness of the blade design method, and can promote the research and development of tidal energy under the conditions of low flow velocity and small radius.

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5

Zhang, Jing, Fan Wu, Chun Wang, Ziyue Mei, An Han, and Danmei Xie. "The Effect of Suction Side Tubercles on Torque Output of a Steam Turbine Low-Pressure Last Stage Blade." Energies 13, no. 8 (April 13, 2020): 1889. http://dx.doi.org/10.3390/en13081889.

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Flow separation and different kinds of stall flows occur under low load conditions for steam turbine last stage blades. In order to delay the flow separation and increase turbine power production, we applied suction side tubercles on steam turbine low-pressure last stage blades in the present study. The amplitude, wavelength, position, and thickness were considered as our design variables. We used the orthogonal test method (OTM) to generate modified blades with different tubercle variables that were then numerically simulated by a three-dimensional computational fluid dynamics (CFD) analysis. The blade axial torque of the nine modified tests was compared with the original blade. The results showed that the application of bionic tubercles on the suction side of the steam turbine blade is a promising solution to improve the blade axial torque for all modified tests with a maximum increase of 33.32% due to the turbulent vortices generated by bionic tubercles.

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6

Nowinski, M., and J. Panovsky. "Flutter Mechanisms in Low Pressure Turbine Blades." Journal of Engineering for Gas Turbines and Power 122, no. 1 (October 20, 1999): 82–88. http://dx.doi.org/10.1115/1.483179.

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The work described in this paper is part of a comprehensive research effort aimed at eliminating the occurrence of low pressure turbine blade flutter in aircraft engines. The results of fundamental unsteady aerodynamic experiments conducted in an annular cascade are studied in order to improve the overall understanding of the flutter mechanism and to identify the key flutter parameters. In addition to the standard traveling wave tests, several other unique experiments are described. The influence coefficient technique is experimentally verified for this class of blades. The beneficial stabilizing effect of mistuning is also directly demonstrated. Finally, the key design parameters for flutter in low pressure turbine blades are identified. In addition to the experimental effort, correlating analyses utilizing linearized Euler methods demonstrate that these computational techniques are adequate to predict turbine flutter. [S0742-4795(00)01301-6]

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7

Pullan, Graham, and Neil W. Harvey. "Influence of Sweep on Axial Flow Turbine Aerodynamics at Midspan." Journal of Turbomachinery 129, no. 3 (July 14, 2006): 591–98. http://dx.doi.org/10.1115/1.2472397.

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Sweep, when the stacking axis of the blade is not perpendicular to the axisymmetric streamsurface in the meridional view, is often an unavoidable feature of turbine design. Although a high aspect ratio swept blade can be designed to achieve the same pressure distribution as an unswept design, this paper shows that the swept blade will inevitably have a higher profile loss. A modified Zweifel loading parameter, taking sweep into account, is first derived. If this loading coefficient is held constant, it is shown that sweep reduces the required pitch-to-chord ratio and thus increases the wetted area of the blades. Assuming fully turbulent boundary layers and a constant dissipation coefficient, the effect of sweep on profile loss is then estimated. A combination of increased blade area and a raised pressure surface velocity means that the profile loss rises with increasing sweep. The theory is then validated using experimental results from two linear cascade tests of highly loaded blade profiles of the type found in low-pressure aeroengine turbines: one cascade is unswept, the other has 45deg of sweep. The swept cascade is designed to perform the same duty with the same loading coefficient and pressure distribution as the unswept case. The measurements show that the simple method used to estimate the change in profile loss due to sweep is sufficiently accurate to be a useful aid in turbine design.

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8

Maulana, Muhammad Ilham, Ahmad Syuhada, and Fiqih Almas. "Computational Fluid Dynamic Predictions on Effects of Screw Number on Performance of Single Blade Archimedes Screw Turbine." E3S Web of Conferences 67 (2018): 04027. http://dx.doi.org/10.1051/e3sconf/20186704027.

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One of the alternative solutions to reduce the impact of electricity crisis in Aceh and other isolated areas in Indonesia is by the construction of small-scale hydro power plants that can work efficiently on the heads lower than 10 meters. One suitable type of turbine applied to the head below 10 meters is the Archimedes screw turbine. Due to the lack of information about the application of low head power plants, resulting in applications of this type of turbine is still less in Indonesia. This paper examined the appropriate turbine model. Before experimental turbine testing, turbines were designed theoretically first and then analyzed numerically. The flow velocity and pressure patterns within the turbine were analyzed using ANSYS CFD (Computational Fluid Dynamic) software under design conditions for 7, 9 and 11 screw numbers for single blade turbine. Based on the results of pressure analysis, speed and turbulent kinetic energy, it found that turbine performance using 11 blades is better among the three turbines. However, the highest average speed was obtained on the turbine using 7 screws, which maximum pressure obtained on a turbine 7 screws of 1406 Pa, on 9 screws on plane 1301 Pa and at 11 screws of 1175 Pa. Based on the results of the analysis, it showed that the smaller the distance between the channel and turbine blades, the results were more efficient due to the absence of wasted streams. Therefore, the flow pressure in the inlet position all directly leaded to the tip off the blade to produce a momentum.

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9

Vogt, Damian M., and Torsten H. Fransson. "Experimental Investigation of Mode Shape Sensitivity of an Oscillating Low-Pressure Turbine Cascade at Design and Off-Design Conditions." Journal of Engineering for Gas Turbines and Power 129, no. 2 (August 7, 2006): 530–41. http://dx.doi.org/10.1115/1.2436567.

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The effect of negative incidence operation on mode shape sensitivity of an oscillating low-pressure turbine rotor blade row has been studied experimentally. An annular sector cascade has been employed in which the middle blade has been made oscillating in controlled three-dimensional rigid-body modes. Unsteady blade surface pressure data were acquired at midspan on the oscillating blade and two pairs of nonoscillating neighbor blades and reduced to aeroelastic stability data. The test program covered variations in reduced frequency, flow velocity, and inflow incidence; at each operating point, a set of three orthogonal modes was tested such as to allow for generation of stability plots by mode recombination. At nominal incidence, it has been found that increasing reduced frequency has a stabilizing effect on all modes. The analysis of mode shape sensitivity yielded that the most stable modes are of bending type with axial to chordwise character, whereas high sensitivity has been found for torsion-dominated modes. Negative incidence operation caused the flow to separate on the fore pressure side. This separation was found to have a destabilizing effect on bending modes of chordwise character, whereas an increase in stability could be noted for bending modes of edgewise character. Variations of stability parameter with inflow incidence have hereby found being largely linear within the range of conditions tested. For torsion-dominated modes, the influence on aeroelastic stability was close to neutral.

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10

Kosowski, Krzysztof, and Marian Piwowarski. "Design Analysis of Micro Gas Turbines in Closed Cycles." Energies 13, no. 21 (November 5, 2020): 5790. http://dx.doi.org/10.3390/en13215790.

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The problems faced by designers of micro-turbines are connected with a very small volume flow rate of working media which leads to small blade heights and a high rotor speed. In the case of gas turbines this limitation can be overcome by the application of a closed cycle with very low pressure at the compressor inlet (lower than atmospheric pressure). In this way we may apply a micro gas turbine unit of accepted efficiency to work in a similar range of temperatures and the same pressure ratios, but in the range of smaller pressure values and smaller mass flow rate. Thus, we can obtain a gas turbine of a very small output but of the efficiency typical of gas turbines with a much higher power. In this paper, the results of the thermodynamic calculations of the turbine cycles are discussed and the designed gas turbine flow parts are presented. Suggestions of the design solutions of micro gas turbines for different values of power output are proposed. This new approach to gas turbine arrangement makes it possible to build a gas turbine unit of a very small output and a high efficiency. The calculations of cycle and gas turbine design were performed for different cycle parameters and different working media (air, nitrogen, hydrogen, helium, xenon and carbon dioxide).

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Dissertations / Theses on the topic "Low pressure turbine blade design"

1

McQuilling, Mark W. "DESIGN AND VALIDATION OF A HIGH-LIFT LOW-PRESSURE TURBINE BLADE." Wright State University / OhioLINK, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=wright1189792837.

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2

Dickel, Jacob Allen. "Design Optimization of a Non-Axisymmetric Endwall Contour for a High-Lift Low Pressure Turbine Blade." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1534980581177159.

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Hansen, Laura C. "Phase Locked Flow Measurements of Steady and Unsteady Vortex Generator Jets in a Separating Boundary Layer." Diss., CLICK HERE for online access, 2005. http://contentdm.lib.byu.edu/ETD/image/etd763.pdf.

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4

Hollon, Brian. "EXPERIMENTAL INVESTIGATION OF SEPARATION IN A LOW PRESSURE TURBINE BLADE CASCADE MODEL." UKnowledge, 2003. http://uknowledge.uky.edu/gradschool_theses/304.

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The flow field around a low pressure turbine blade is examined using smoke-wire flow visualization, static surface pressure measurements, and particle image velocimetry (PIV). The purpose of the experimental study is to investigate the transition and separation characteristics on low pressure turbine blades under low Reynolds number (Re) and varying freestream turbulence intensity (FSTI). A cascade model consisting of 6 Pratt andamp; Whitney PAK-B low pressure turbine blades was examined in a wind tunnel using PIV and flow visualization. Smoke-wire visualization was performed for test section exit angles of 93°, 95°, and 97°, in the range Re = 3 · 104 to 9 · 104 and three levels of FSTI varied with a passive grid. The locations of separation and transition were determined to be approximately 45% and 77% of the suction surface length, respectively, based upon the smoke stream lines observed in the images, and appear to be independent of Re, turning angle, and FSTI. The maximum size of the separation bubble was found to decrease with increasing Re, turning angle, and FSTI. PIV images from three camera views were processed for an exit angle of 95° and a Re range of 3:0 · 104 to 30:0 · 104 and three levels of FSTI. Velocity, vorticity, and reversed flow probability field plots were generated along with velocity, vorticity, and RMS velocity profiles. The point of separation point was determined to be from 63% SSL to 67% SSL. The area of reversed flow was computed for each image pair from camera views 1 and 3, as an approxiamtion of the relative size of the separation region. For low Re and FSTI cases the area was much larger than for higher FSTI cases at any Re. The raw PIV images include some of the rst clear pictures of the turbulent flow structures forming in the unsteady shear layer over the suction surface of low pressure turbine blades. Several movies are compiled that show how the geometry and location of the shear layer evolve in time for a given set of flow conditions.

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Ramakumar, Karthik. "ACTIVE FLOW CONTROL OF LOW PRESSURE TURBINE BLADE SEPARATION USING PLASMA ACTUATORS." UKnowledge, 2006. http://uknowledge.uky.edu/gradschool_theses/359.

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The current study examines plasma actuators as flow control devices. The actuators are placed on a turbine blade profile in a 2D turbine cascade for separation flow control. The configuration involves copper strips separated by a layer of dielectric material, across which an AC electric potential in the range of 5 kHz and 5 kV is applied. The efficiency of the actuator is monitored by measuring power input and flow control effectiveness. Preliminary observations are performed for a quiescent case on a flat plate profile to analyze the average and instantaneous velocities generated by the actuator for varied input parameters, such as waveform shape and frequency. Observations include the generation of starting and standing vortices that may be leveraged for unsteady flow control applications. In the case of turbine flow control, the Pratt andamp; Whitney Pak-B blade profile is used to determine the actuator performance for separation reduction at Reynolds number O(104). The results are compared with flow control on and off states for varied actuator input frequency, power, duty cycle and freestream velocity. Pressure measurements are conducted for the actuated case that show reduced separation and increased main flow velocity. Experimental diagnostics include PIV, 7-hole probe, and smoke-wire flow visualization techniques. Phase locked PIV performed at different forcing frequencies reveals the generation of cross-stream vortices providing re-attachment of the separated flow. During the off periods of the cycle the region of separation is observed to creep back to its original separation point. Various fields-of-view show the structure of these cross-stream vortices at different phases. While the actuator is seen to accelerate the flow in the immediate region of the plasma, the generation of starting vortices demonstrates that unsteady actuation is a more effective form of flow control.

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6

Bury, Mark Eric. "Influence of Reynolds number and blade geometry on low pressure turbine performance." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/50310.

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7

Verona, Claire L. "Stress corrosion cracking of low pressure steam turbine blade and rotor materials." Thesis, Loughborough University, 2012. https://dspace.lboro.ac.uk/2134/10165.

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Stress corrosion cracking of a 14 wt% Cr martensitic stainless steel, with commercial names PH-15Cr5Ni, FV520B or X4CrNiCuMo15-5, used for the manufacture of low pressure turbine blades, has been studied with the intention of gaining a better understanding of the processes involved, how they occur and why. Industrially this is very important as stress corrosion cracking is considered to be a delayed failure process, whereby microscopic cracks can potentially propagate through a metal undetected until catastrophic failure occurs. The aim of this work is to establish links between crack length and external factors, such as exposure time, in order to devise a method of dating stress corrosion cracks and therefore predicting their possible occurrence in-service.

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8

He, Binyan. "Fatigue crack growth behaviour in a shot peened low pressure steam turbine blade material." Thesis, University of Southampton, 2015. https://eprints.soton.ac.uk/388077/.

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9

Wang, Yuchen. "Blade Design of Vertical Axis Wind Turbine at Low Tip-speed-ratios." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1524224348317784.

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10

McQuilling, Mark. "EXPERIMENTAL STUDY OF ACTIVE SEPARATION FLOW CONTROL IN A LOW PRESSURE TURBINE BLADE CASCADE MODEL." UKnowledge, 2004. http://uknowledge.uky.edu/gradschool_theses/320.

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The flow field around a low pressure turbine (LPT) blade cascade model with and without flow control is examined using ejector nozzle (EN) and vortex generator jet (VGJ) geometries for separation control. The cascade model consists of 6 Pak-B Pratt andamp; Whitney low pressure turbine blades with Re = 30,000-50,000 at a free-stream turbulence intensity of 0.6%. The EN geometry consists of combined suction and blowing slots near the point of separation. The VGJs consist of a row of holes placed at an angle to the free-stream, and are tested at two locations of 69% and 10.5% of the suction surface length (SSL). Results are compared between flow control on and flow control off states, as well as between the EN, VGJs, and a baseline cascade with no flow control geometry for steady and pulsatile blowing. The EN geometry is shown to control separation with both steady and pulsatile blowing. The VGJs at 69% SSL are shown to be much more aggressive than the EN geometry, achieving the same level of separation control with lower energy input. Pulsed VGJs (PVGJ) have been shown to be just as effective as steady VGJs, and results show that a 10% duty cycle is almost as effective as a 50% duty cycle. The VGJs at 10.5% SSL are shown to be inefficient at controlling separation. No combination of duty cycle and pulsing frequency tested can eliminate the separation region, with only higher steady blowing rates achieving separation control. Thus, the VGJs at 69% SSL are shown to be the most effective in controlling separation.

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Books on the topic "Low pressure turbine blade design"

1

Detached Eddy Simulation Analysis of Pak-B Low Pressure Turbine Blade. Storming Media, 2004.

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J, Dorney Daniel, and NASA Glenn Research Center, eds. Experimental and numerical investigation of losses in low-pressure turbine blade rows. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Experimental and numerical investigation of losses in low-pressure turbine blade rows. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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4

Use of Dimples to Suppress Boundary Layer Separation on a Low Pressure Turbine Blade. Storming Media, 2002.

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Effect of Dimple Pattern on the Suppression of Boundary Layer Separation on a Low Pressure Turbine Blade. Storming Media, 2004.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. STUDY OF LOW REYNOLDS NUMBER EFFECTS ON THE LOSSES IN LOW-PRESSURE TURBINE BLADE ROWS... NASA/TM-1998-207919... SEP. 16, 1998. [S.l: s.n., 1999.

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Book chapters on the topic "Low pressure turbine blade design"

1

Raverdy, B., I. Mary, P. Sagaut, and J. M. Roux. "LES of Wake-Blade Interference in a Low-Pressure Turbine." In Direct and Large-Eddy Simulation V, 627–34. Dordrecht: Springer Netherlands, 2004. http://dx.doi.org/10.1007/978-1-4020-2313-2_66.

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Sayma, A. I., M. Vahdati, J. S. Green, and M. Imregun. "Whole-Assembly Flutter Analysis of a Low Pressure Turbine Blade." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 347–59. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_23.

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Raverdy, B., I. Mary, P. Sagaut, and N. Liamis. "Large-Eddy Simulation of the Flow around a Low Pressure Turbine Blade." In Direct and Large-Eddy Simulation IV, 381–88. Dordrecht: Springer Netherlands, 2001. http://dx.doi.org/10.1007/978-94-017-1263-7_46.

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Habel, Ulrike, Falko Heutling, Claudia Kunze, Wilfried Smarsly, Gopal Das, and Helmut Clemens. "Forged Intermetallic γ-TiAl Based Alloy Low Pressure Turbine Blade in the Geared Turbofan." In Proceedings of the 13th World Conference on Titanium, 1223–27. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119296126.ch208.

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More, Aarti, and Anindita Roy. "Design and Weight Minimization of Small Wind Turbine Blade for Operation in Low-Wind Areas." In Advances in Energy Research, Vol. 2, 311–22. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-2662-6_29.

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Balijepalli, Ramakrishna, V. P. Chandramohan, and K. Kirankumar. "Design and Performance Investigation of Wind Turbine Blade for Solar Updraft Tower Under Low Wind Speeds." In Advances in Energy Research, Vol. 2, 283–95. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-2662-6_27.

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Kim, Chul Su, Jung Kyu Kim, and Tae Seong Kim. "An Evaluation of Appropriate Probabilistic S-N Curve for the Turbine Blade Steel in the Low Pressure Steam." In Key Engineering Materials, 1751–57. Stafa: Trans Tech Publications Ltd., 2005. http://dx.doi.org/10.4028/0-87849-978-4.1751.

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Mundt, G., A. Neidel, B. Matijasevic-Lux, and J. Fritsche. "Moving Blade Failure in the Low-Pressure Turbine of a Steam Turbo SetSchaufelschaden in der Niederdruckteilturbine eines Dampfturbosatzes." In Schadensfallanalysen metallischer Bauteile, 127–38. München: Carl Hanser Verlag GmbH & Co. KG, 2015. http://dx.doi.org/10.3139/9783446446090.010.

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Ludewig, Tom, Reinhard Niehuis, and Matthias Franke. "Comparison of the Capability of Active and Passive Methods of Boundary Layer Control on a Low Pressure Turbine Cascade." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 191–98. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14243-7_24.

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Miura, Nobuhiro, and Yoshihiro Kondo. "Morphology of γ′ Precipitates in a First Stage Low Pressure Turbine Blade of a Ni-Based Superalloy after Service and after Following Aging." In 18th International Federation for Heat Treatment and Surface Engineering, 205–17. 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959: ASTM International, 2011. http://dx.doi.org/10.1520/stp49433t.

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Conference papers on the topic "Low pressure turbine blade design"

1

Panovsky, Josef, and Robert E. Kielb. "A Design Method to Prevent Low Pressure Turbine Blade Flutter." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-575.

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A design approach to avoid flutter of low pressure turbine blades in aircraft engines is described. A linearized Euler analysis, previously validated using experimental data, is used for a series of parameter studies. The influence of mode shape and reduced frequency are investigated. Mode shape is identified as the most important contributor to determining the stability of a blade design. A new stability parameter is introduced to gain additional insight into the key contributors to flutter. This stability parameter is derived from the influence coefficient representation of the cascade, and includes only contributions from the reference blade and its immediate neighbors. This has the effect of retaining the most important contributions to aerodynamic damping while filtering out terms of less significance. This parameter is utilized to develop a stability map, which provides the critical reduced frequency as a function of torsion axis location. Rules for preliminary design and procedures for detailed design analysis are defined.

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Curtis, E. M., H. P. Hodson, M. R. Banieghbal, J. D. Denton, R. J. Howell, and N. W. Harvey. "Development of Blade Profiles for Low Pressure Turbine Applications." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-358.

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This paper describes a programme of work, largely experimental, which was undertaken with the objective of developing an improved blade profile for the low-pressure turbine in aero-engine applications. Preliminary experiments were conducted using a novel technique. An existing cascade of datum blades was modified to enable the pressure distribution on the suction surface of one of the blades to be altered. Various means, such as shaped inserts, an adjustable flap at the trailing edge, and changing stagger were employed to change the geometry of the passage. These experiments provided boundary layer and lift data for a wide range of suction surface pressure distributions. The data was then used as a guide for the development of new blade profiles. The new blade profiles were then investigated in a low-speed cascade that included a set of moving bars upstream of the cascade of blades 10 simulate the effect of the incoming wakes from the previous blade row in a multistage turbine environment. Results are presented for two improved profiles that are compared with a datum representative of current practice. The experimental results include loss measurements by wake traverse, surface pressure distributions, and boundary layer measurements. The cascades were operated over a Reynolds Number range from 0.7 × 105 to 4.0 × 105. The first profile is a “laminar flow” design that was intended to improve the efficiency at the same loading as the datum. The other is a more highly loaded blade profile intended to permit a reduction in blade numbers. The more highly loaded profile is the most promising candidate for inclusion in future designs. It enables blade numbers to be reduced by 20%, without incurring any efficiency penalty. The results also indicate that unsteady effects must be taken into consideration when selecting a blade profile for the low-pressure turbine.

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Giovannini, Matteo, Michele Marconcini, Filippo Rubechini, Andrea Arnone, and Francesco Bertini. "Scaling 3D Low-Pressure Turbine Blades for Low-Speed Testing." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42176.

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The present activity was carried out in the framework of the Clean Sky European research project ITURB (“Optimal High-Lift Turbine Blade Aero-Mechanical Design”), aimed at designing and validating a turbine blade for a geared open rotor engine. A cold-flow, large-scale, low-speed (LS) rig was built in order to investigate and validate new design criteria, providing reliable and detailed results while containing costs. This paper presents the design of a LS stage, and describes a general procedure that allows to scale 3D blades for low-speed testing. The design of the stator row was aimed at matching the test-rig inlet conditions and at providing the proper inlet flow field to the blade row. The rotor row was redesigned in order to match the performance of the high-speed one, compensating for both the compressibility effects and different turbine flow paths. The proposed scaling procedure is based on the matching of the 3D blade loading distribution between the real engine environment and the LS facility one, which leads to a comparable behavior of the boundary layer and hence to comparable profile losses. To this end, the datum blade is parameterized, and a neural-network-based methodology is exploited to guide an optimization process based on 3D RANS computations. The LS stage performance were investigated over a range of Reynolds numbers characteristic of modern low-pressure turbines by using a multi-equation, transition-sensitive, turbulence model.

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Bons, Jeffrey P., Laura C. Hansen, John P. Clark, Peter J. Koch, and Rolf Sondergaard. "Designing Low-Pressure Turbine Blades With Integrated Flow Control." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68962.

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A low pressure turbine blade was designed to produce a 17% increase in blade loading over an industry-standard airfoil using integrated flow control to prevent separation. The design was accomplished using two-dimensional CFD predictions of blade performance coupled with insight gleaned from recently published work in transition modeling and from previous experiments with flow control using vortex generator jets (VGJs). In order to mitigate the Reynolds number lapse in efficiency associated with LPT airfoils, a mid-loaded blade was selected. Also, separation predictions from the computations were used to guide the placement of control actuators on the blade suction surface. Three blades were fabricated using the new design and installed in a two-passage linear cascade facility. Flow velocity and surface pressure measurements taken without activating the VGJs indicate a large separation bubble centered at 68% axial chord on the suction surface. The size of the separation and its growth with decreasing Reynolds number agree well with CFD predictions. The separation bubble reattaches to the blade over a wide range of inlet Reynolds numbers from 150,000 down to below 20,000. This represents a marked improvement in separation resistance compared to the original blade profile which separates without reattachment below a Reynolds number of 40,000. This enhanced performance is achieved by increasing the blade spacing while simultaneously adjusting the blade shape to make it less aft-loaded but with a higher peak cp. This reduces the severity of the adverse pressure gradient in the uncovered portion of the modified blade passage. With the use of pulsed VGJs, the design blade loading was achieved while providing attached flow over the entire range of Re. Detailed phase-locked flow measurements using three-component PIV show the trajectory of the jet and its interaction with the unsteady separation bubble. Results illustrate the importance of integrating flow control into the turbine blade design process and the potential for enhanced turbine performance.

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Ambrish and Nand Kumar Singh. "Development of LP Blade Module for High Back Pressure-Aerodynamic Design." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4542.

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In steam turbine power plants, the appropriate design of the last stage blades is critical in determining the plant efficiency and reliability. The development of LP module for desert applications is finding applications for a number of industrial steam turbine operating with air cooled condensers. The conventional LP Module for water cooled condenser operates at low back pressure (Pexit = 0.09 bar) and are generally not suitable for high back pressure application. This paper focuses on the aerodynamic design & optimization of last stages of LP blade module for high back pressure application and validation through 3D CFD. The guide and moving blade are designed with seven equally-spaced profiles section from hub to shroud through Axstream S/w. The profile and incidence losses are minimized for the design and off-design conditions. Aeromechanical design of LP blade module consisting of 2 stages for 0.2 bar back pressure, 1.1 bar inlet static pressure and a mass flow of 61.2 kg/s is carried out. An optimization process through a streamline curvature code and design optimization software using Optimus is established and flow path contours is optimized thoroughly, a total to total efficiency of 81.4% is achieved for the rated condition. The off-design performance is investigated for a wide range of operating conditions, especially at low volume flow rate of steam condition.

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Carolus, Thomas H., and Ralf Starzmann. "An Aerodynamic Design Methodology for Low Pressure Axial Fans With Integrated Airfoil Polar Prediction." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45243.

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A common blade design methodology for low solidity fan rotors is based on blade element theory combined with empirical airfoil lift and drag data. Often the required airfoil characteristics have to be estimated from existing wind tunnel data, roughly estimating the effects of Reynolds number and airfoil modifications such as trailing edge thickening. This contribution presents an extension of that methodology: Polar curves are computed during the fan design procedure and applied to each blade element. Reynolds and even Mach number as well as all geometrical features of the airfoil are fully taken into account. For that the public domain code XFOIL for analysis of subsonic isolated airfoils by Drela and Youngren has been integrated in an existing blade design code. The paper summarizes blade element theory and points out the interface where XFOIL data enter. A case study demonstrates how the airfoil specification affects the fan blade design. Two fan rotors for the same duty point but with NACA 4512 and FX60-126 airfoil blades are compared. Moreover, the effect of trailing edge bluntness on the blade shape is investigated.

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Coull, John D., and Howard P. Hodson. "Blade Loading and its Application in the Mean-Line Design of Low Pressure Turbines." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45238.

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In order to minimize the number of iterations to a turbine design, reasonable choices of the key parameters must be made at the earliest possible opportunity. The choice of blade loading is of particular concern in the low pressure (LP) turbine of civil aero engines, where the use of high-lift blades is widespread. This paper presents an analytical mean-line design study for a repeating-stage, axial-flow Low Pressure (LP) turbine. The problem of how to measure blade loading is first addressed. The analysis demonstrates that the Zweifel coefficient [1] is not a reasonable gauge of blade loading because it inherently depends on the flow angles. A more appropriate coefficient based on blade circulation is proposed. Without a large set of turbine test data it is not possible to directly evaluate the accuracy of a particular loss correlation. The analysis therefore focuses on the efficiency trends with respect to flow coefficient, stage loading, lift coefficient and Reynolds number. Of the various loss correlations examined, those based on Ainley and Mathieson ([2], [3], [4]) do not produce realistic trends. The profile loss model of Coull and Hodson [5] and the secondary loss models of Craig and Cox [6] and Traupel [7] gave the most reasonable results. The analysis suggests that designs with the highest flow turning are the least sensitive to increases in blade loading. The increase in Reynolds number lapse with loading is also captured, achieving reasonable agreement with experiments.

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Nowinski, M., and J. Panovsky. "Flutter Mechanisms in Low Pressure Turbine Blades." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-573.

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The work described in this paper is part of a comprehensive research effort aimed at eliminating the occurrence of low pressure turbine blade flutter in aircraft engines. The results of fundamental unsteady aerodynamic experiments conducted in an annular cascade are studied in order to improve the overall understanding of the flutter mechanism and to identify the key flutter parameters. In addition to the standard traveling wave tests, several other unique experiments are described. The influence coefficient technique is experimentally verified for this class of blades. The beneficial stabilizing effect of mistuning is also directly demonstrated. Finally, the key design parameters for flutter in low pressure turbine blades are identified. In addition to the experimental effort, correlating analyses utilizing linearized Euler methods demonstrate that these computational techniques are adequate to predict turbine flutter.

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Park, Jong-Po, Zili Xu, and Seok-Ju Ryu. "Fracture Analysis and Retrofit Design of 1st Stage Blades for a Low-Pressure Steam Turbine." In ASME 2003 International Mechanical Engineering Congress and Exposition. ASMEDC, 2003. http://dx.doi.org/10.1115/imece2003-41137.

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Cracking of blade fingers occurred in a few numbers of 1st stage blades for low-pressure steam turbines. In order to find out the fault mechanism, one of the cracked blades has been inspected. The inspection results showed that the cracking blades has been inspected. The inspection results showed that the cracking of the blade finger was caused by high cycle fatigue. Vibratory modes of the blade group have been calculated and measured using a 3-D finite element S/W and impact test, respectively. The results showed that resonance of the second type group axial vibration mode with nozzle passing frequency was the source of high cycle fatigue load. To avoid the dangerous resonance, the blade groups have been modified into 10 blades per group. The new blade groups have been operated safely more than one year since the modification.

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Watanabe, Fumiaki, Takeshi Nakamura, and Ken-ichi Shinohara. "The Application of Ceramic Matrix Composite to Low Pressure Turbine Blade." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56614.

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The structural reliability of composite parts for aircraft is established through the “building block” approach, which is a series of tests that are conducted using specimens of various levels of complexity. In this approach, the failure modes and criteria are validated step by step with tests and analysis at coupon, element, sub-component, and component levels. IHI is developing ceramic matrix composite (CMC) components for aircraft engines to realize performance improvement and weight reduction. We conducted the concept design of CMC low pressure turbine (LPT) blade with the building block approach. In this paper, we present the processes and results of the design, which was supported by a series of tests. Typical low pressure turbine blade has dovetail, airfoil and tip shroud. Each element has different function and characteristic shape. In order to select the configuration of CMC LPT blade, we conducted screening tests for each element. The function of dovetail is to sustain the connection with blade and disk against centrifugal force. The failure modes and strength of dovetail elements were examined by static load tests and cyclic load tests. The configuration of airfoil was selected by modal tests. The function of tip shroud is forming gas passage and reducing the leakage flow, therefore this portion needs to sustain the shape against the centrifugal force and the rubbing force. The feasibility of tip shroud was verified by spin tests and rubbing tests. The initial CMC LPT blades were designed as combination of the selected elements by these screening tests. Prototype parts were made and tested to check the manufacturability and the structural feasibility. The static strength to the centrifugal force was examined by spin test. The durability to vibration was examined by HCF test.

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Reports on the topic "Low pressure turbine blade design"

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Advanced turbine systems program conceptual design and product development: Task 8.1, Low-pressure drop recuperator. Office of Scientific and Technical Information (OSTI), September 1995. http://dx.doi.org/10.2172/204084.

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