Off-Design Performance of a Single Stage Transonic Turbine

Woinowsky-Krieger, M.; Lavoie, Jonathan; Vlasic, E. P.; Moustapha, S. H.

doi:10.1115/98-gt-002

Cited by 4 publications

(3 citation statements)

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“…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. Recently, the performance testing of a cooled transonic high-pressure turbine with a loading factor of 1.9 was conducted by Neumayer et al [10].…”

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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“…In a paper of He,21 it was also mentioned that the non-twist rotor blades lead to a negative incidence near the tip and a positive incidence near the hub. Woinowsky-Krieger et al 5 reported that a transonic turbine had an 8% increase in the blade incidence as the turbine rotational speed changed from 100% to 80%. This is considered to be qualitatively in accordance with the results presented in Figure 10(a).…”

Section: Stator Flow Fields At Different Operating Conditionsmentioning

confidence: 98%

“…In a paper of Woinowsky-Krieger et al, 5 a transonic axial turbine was studied both experimentally and numerically. They found out that the turbine efficiency was only mildly affected by the pressure ratio.…”

Section: Introductionmentioning

confidence: 99%

Performance and flow fields of a supersonic axial turbine at off-design conditions

Grönman

Turunen-Saaresti

Röyttä

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part A:

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The increasing demand of energy efficiency and the utilisation of small-scale energy sources require efficient, small and versatile turbines. Supersonic turbines have a high power density and therefore small size and fewer stages than the subsonic ones. However, the performance of a supersonic turbine can decrease rapidly when operating at off-design conditions. This raises a need for the improvement of the turbine off-design performance. In this article, a supersonic axial flow turbine is studied numerically to find the causes of efficiency decrement. This article presents the most thorough study so far about the reasons that lead to the decreased off-design performance with supersonic axial flow turbines and explains the loss sources individually for the stator and the rotor. Three operating conditions are studied, and it is suggested that at the lower than design pressure ratios, the shock losses of the stator decrease while simultaneously the stator secondary losses increase. The high positive incidence at the lowest modelled pressure ratio, mass flow and rotational speed caused a significant decrease in the rotor and stage performance. This highlights the importance of incidence even in shock-driven supersonic turbine flows.

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