Effect of Rotor Tip Clearance and Configuration on Overall Performance of a 12.77-Centimeter Tip Diameter Axial-Flow Turbine

Haas, J. E.; Kofskey, M. G.

doi:10.1115/79-gt-42

Cited by 7 publications

(6 citation statements)

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“…The present result agrees with the study of Haas and Kofskey [5] and Bindon [6] which determined a linear variation of performance with the clearance gap although they predicted a nonlinear relation for gaps less than 1% of chord.…”

Section: Resultssupporting

confidence: 92%

Axial Turbine Performance Estimation During Dynamic Operations

Nicoară

Vilag

et al. 2020

Int. J. Aeronaut. Space Sci.

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During service, a turbine engine undergoes frequently dynamic operations. Because of the changes in mass flow, temperature, pressure, as well as the different reaction of the components of turbine to these changes, the turbine performances may vary significantly. It is critical to understand and quantify these variations to design and integrate the turbine to the engine. This paper presents a study of the performances and the variation of the performances for an axial gas turbine across its operating envelope. Numerical simulations are used to describe the flow across the turbine and to estimate the turbine maps. Using theoretical charts for typical turbine thermal expansion, the variation of tip clearance across the working line is approximated. Because of the changes of the tip clearance, using a single geometry may not supply relevant information during real dynamic operations. In order to eliminate these additional errors in the numerical study, a number of turbines maps are recalculated for different tip clearances, respectively to engine regimes. With the resulting data, the working line is recalculated across multiple maps. The comparison between the two working lines is presented as well as the study of performance variation of the turbine across the operation envelope and the influence of tip clearance at different regimes.

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Section: Resultssupporting

confidence: 92%

Axial Turbine Performance Estimation During Dynamic Operations

Nicoară

Vilag

et al. 2020

Int. J. Aeronaut. Space Sci.

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“…Figure 8 shows the variation of turbine efficiency with Assuming a linear variation of efficiency with tip clearance, then the above table indicates an efficiency change of 2.6 percentage points for a 1.0 percentage point change of tip clearance/mean blade height ratio. This rate of exchange is considerably higher than quoted for a moderately loaded turbine by Patel [2] and is in better agreement with results for high reaction tip sections quoted by Haas and Kofskey [7]. It probably reflects the increased tip leakage which is likely to result with a more highly loaded tip section as present on the test turbine.…”

Section: Test Resultssupporting

confidence: 78%

The Design, Performance and Analysis of a High Work Capacity Transonic Turbine

Bryce¹,

Litchfield²,

Leversuch³

1985

Journal of Engineering for Gas Turbines and Power

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The Design, Performance and Analysis of a High Work Capacity Transonic Turbine This paper describes the design and testing of a high work capacity single-stage transonic turbine of aerodynamic duty tailored to the requirements of driving the high-pressure core of a low cost turbofan engine. Aerodynamic loading was high for this duty (AH/U 2 =2.1) and a major objective in the design was the control of the resulting transonic flow to achieve good turbine performance. Practical and coolable blading was a design requirement. At the design point (pressure ratio = 4.48), a turbine total to total efficiency of 87.0 percent was measured -this being based on measured shaft power and a tip clearance of 1.4 percent of blade height. In addition, the turbine was comprehensively instrumented to allow measurement of aerofoil surface static pressures on both stator and rotor-the latter being expedited via a rotating scanivalve system. Downstream area traverses were also conducted. Analysis of these measurements indicates that the turbine operates at overall reaction levels lower than design but the rotor blade performs efficiently.

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“…The numerical case corresponds to the case considered in (Agromayor and Nord 2019), and present work is validated against this case due to the similarities of the models. The three experimental cases are cold-air tests of one-stage axial turbines, both at subsonic and transonic conditions (Haas and Kofskey 1975;Moffitt et al 1980;Nusbaum and Kofskey 1972).…”

Section: Model Validationmentioning

confidence: 99%

“…The second experimental reference is the case presented in (Haas and Kofskey 1975). The operating conditions and performance parameters are shown in Table 6.…”

Section: Experimental Casementioning

confidence: 99%

Proceedings of the 63rd International Conference of Scandinavian Simulation Society, SIMS 2022, Trondheim, Norway, September 20-21, 2022

2022

Linköping Electronic Conference Proceedings

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Effect of Rotor Tip Clearance and Configuration on Overall Performance of a 12.77-Centimeter Tip Diameter Axial-Flow Turbine

Cited by 7 publications

References 0 publications

Axial Turbine Performance Estimation During Dynamic Operations

Axial Turbine Performance Estimation During Dynamic Operations

The Design, Performance and Analysis of a High Work Capacity Transonic Turbine

Proceedings of the 63rd International Conference of Scandinavian Simulation Society, SIMS 2022, Trondheim, Norway, September 20-21, 2022

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