The Design and Performance of a High Work Research Turbine

Vlasic, E. P.; Girgis, Sami; Moustapha, S. H.

doi:10.1115/95-gt-233

Cited by 8 publications

(8 citation statements)

References 6 publications

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“…Moustapha et al [7] (Highly Loaded Turbine) showed the effect of blade loading on high loaded ( H /U 2 = 2.4) stage efficiency at off-design conditions; increase in the rotor blade loading by 53 per cent reduced the efficiency by 2.5 per cent. Vlasic et al [8] (High Work Research Turbine) investigated a single-stage turbine with a pressure ratio of 5 and stage loading of 2.2, the efficiency is reduced by 2.1 per cent when the turbine-cooling rate goes from 0 to 11 per cent. Woinowsky-Krieger et al [9] showed that a 10 per cent reduction in the rotational speed resulted in a decrease of 3 per cent in the efficiency for a single-stage transonic turbine.…”

Section: Introductionmentioning

confidence: 98%

Performance analysis of a transonic high-pressure turbine

Yasa

Paniagua

Bussolin³

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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Efficiency is a crucial design parameter in any turbine development. This research presents a detailed investigation on the efficiency of a modern transonic high-pressure turbine. The work focuses on the study of the efficiency loss at different stage loading factors (ranging from H /U 2 = 1.3 to 2.7) and various flow factors (V ax /U = 0.41 to 0.90). In particular, the present research is of utmost importance to understand the effect of the vane trailing edge shocks in the turbine stage efficiency.The experimental work was carried out in a compression tube facility that allows testing of the turbine at temperature ratios, Re and Mach numbers, encountered in real engines. The efficiency is measured by the mechanical method. Experiments were performed with two different vanes (cooled and uncooled) at two stagger angles, four rotational speeds (4570-6500 r/min) and three pressure ratios (p 01 /p s3 ranging from 2.42 to 5.12). The effect of the change of reaction and rotor incidence is correlated with the performance. Three-dimensional Navier-Stokes calculations aid the interpretation of the results.

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Section: Introductionmentioning

confidence: 98%

Performance analysis of a transonic high-pressure turbine

Yasa

Paniagua

Bussolin³

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…Rich experience was accumulated through the investigation, however, the shape of the blade was all convergent ones and the loss level was high to some extent. High work gas turbines [15][16][17][18] were investigated with the stage pressure ratio higher than 3. The highest outlet Mach number of these turbines was about 1.4.…”

Section: Previous Studies On Transonic Turbinementioning

confidence: 99%

Influence of exit-to-throat width ratio on performance of high pressure convergent-divergent rotor in a vaneless counter-rotating turbine

Zhang

Wang

Wei

et al. 2011

Sci. China Technol. Sci.

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This paper describes the redesign of a high pressure rotor (with exit Mach number around 1.5) for the vaneless counter-rotating turbine by choosing adequate exit-to-throat width ratio. Based on the previous design analysis and test results, effects of the exit-to-throat width ratio on the performance of the transonic turbine cascade were proposed. In order to investigate the influence of the exit-to-throat width ratio on the performance of the turbine cascade, a flow model of the convergent-divergent turbine cascade was constructed by using the theory of Laval nozzle. Then a method on how to choose the adequate exit-to-throat width ratio for the turbine cascade was proposed. To validate the method, it was used to calculate the adequate exit-to-throat width ratio for the high pressure rotor of the vaneless counter-rotating turbine. The high pressure turbine rotor was redesigned with the new exit-to-throat width ratio. Numerical simulation results show that the isentropic efficiency of the redesigned vaneless counter-rotating turbine under the design condition has increased by 0.9% and the efficiencies under the off-design conditions are also improved significantly.On the original design, a group of compressional waves are created from the suction surface after about 60% axial chord in the high pressure turbine rotor. While on the new design the compressional waves are eliminated. Furthermore, on the original design, the inner-extending waves first impinge on the next high pressure turbine rotor suction surface. Its reflection is strong enough and cannot be neglected. However on the new design the inner-extending waves are weakened or even eliminated.Another main progress is that the redesigned high pressure turbine rotor is of practical significance. In the original rotor, a part of the blade (from 60% axial chord to the trailing edge) is thin leading to the intensity problem and difficult arrangement of the cooling system. In the new design, however, the thickness distribution of the rotor airfoil along the chord is relatively reasonable. The intensity of the rotor is enhanced. It is possible to arrange the cooling system reasonably. exit-to-throat width ratio, counter-rotating turbine, transonic turbine, high pressure rotor Citation:Zhang L, Wang H S, Luo W W, et al. Influence of exit-to-throat width ratio on performance of high pressure convergent-divergent rotor in a vaneless counter-rotating turbine.

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“…Mee et al [10], Michelassi et al [12], Bohn et al [14], Kapteijn et al [47], Vlasic et al [48], Sieverding et al [49], and Tanuma et al [50] investigate losses downstream of transonic airfoils with trailing edge ejection. Mee et al [10], Day et al [45], and Osnaghi et al [51] all indicate that density ratio influences are well correlated using the momentum flux ratio.…”

Section: International Journal Of Rotating Machinerymentioning

confidence: 99%

Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

Ligrani

2012

International Journal of Rotating Machinery

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The influences of a variety of different physical phenomena are described as they affect the aerodynamic performance of turbine airfoils in compressible, high-speed flows with either subsonic or transonic Mach number distributions. The presented experimental and numerically predicted results are from a series of investigations which have taken place over the past 32 years. Considered are (i) symmetric airfoils with no film cooling, (ii) symmetric airfoils with film cooling, (iii) cambered vanes with no film cooling, and (iv) cambered vanes with film cooling. When no film cooling is employed on the symmetric airfoils and cambered vanes, experimentally measured and numerically predicted variations of freestream turbulence intensity, surface roughness, exit Mach number, and airfoil camber are considered as they influence local and integrated total pressure losses, deficits of local kinetic energy, Mach number deficits, area-averaged loss coefficients, mass-averaged total pressure loss coefficients, omega loss coefficients, second law loss parameters, and distributions of integrated aerodynamic loss. Similar quantities are measured, and similar parameters are considered when film-cooling is employed on airfoil suction surfaces, along with film cooling density ratio, blowing ratio, Mach number ratio, hole orientation, hole shape, and number of rows of holes.

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The Design and Performance of a High Work Research Turbine

Cited by 8 publications

References 6 publications

Performance analysis of a transonic high-pressure turbine

Performance analysis of a transonic high-pressure turbine

Influence of exit-to-throat width ratio on performance of high pressure convergent-divergent rotor in a vaneless counter-rotating turbine

Aerodynamic Losses in Turbines with and without Film Cooling, as Influenced by Mainstream Turbulence, Surface Roughness, Airfoil Shape, and Mach Number

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