Description of the Warm Core Turbine Facility and the Warm Annular Cascade Facility Recently Installed at NASA Lewis Research Center

Whitney, W. J.; Stabe, R. G.; Moffitt, T. P.

doi:10.4271/801122

Cited by 13 publications

(5 citation statements)

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“…The object selected for the numerical analyses whose results are presented in this paper is the stage of a gas turbine intended for the aircraft industry [9] [10]. This turbine features a single stage only.…”

Section: Analyzed Turbine Stagementioning

confidence: 99%

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The Analysis of the Noise Generation in Gas Turbine Stage

Dykas¹,

Machalica²

2014

OJA

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The aim of this paper is to assess the impact of the mutual positioning of the turbine stage stator and rotor blades on noise generation. The Ansys CFX commercial software package and the Scale-Adaptive Simulation (SAS) hybrid turbulence model are used for numerical analyses. The paper is focused on an analysis that the pressure wave generation resulting from unsteady flow phenomena. In order to present the problem, the Fast Fourier Transformation (FFT) analysis of pressure fluctuation is carried out at selected points of the turbine stage computational domain. A comparison of values of individual components for subsequent control points allows an approximate determination of the place of generation of pressure waves, the direction of their propagation and the damping rate. Moreover, the numerical analyses make it possible to evaluate the justification for the use of the SAS model, which is rather demanding in terms of equipment, in simulations of unsteady flow fields where generation and propagation of noise waves occur.

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Section: Analyzed Turbine Stagementioning

confidence: 99%

“…The numerical analysis was carried out for the turbine design parameters described in a NASA report [10]. The characteristic feature of the turbine is that it has just one stage, which distinguishes it from other turbines used in turbofan engines.…”

Section: Physical and Numericalmentioning

confidence: 99%

The Analysis of the Noise Generation in Gas Turbine Stage

Dykas¹,

Machalica²

2014

OJA

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“…These included the large scale rotating rig (LSRR) [1], NASA warm core turbine test rig (WCTTR) [2], and MIT blow down turbine test Rig (BTTR) [3]. Some researchers also have performed hot streak simulations by numerical method.…”

Section: Introductionmentioning

confidence: 99%

Unsteady numerical simulation of hot streak/blades interaction and film cooling

Xiao

2010

J. Therm. Sci.

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Deeply research on management and application of hot streak is an important way to breakthrough technique obstacle of aero engine hot components. Numerical method is a useful instrument to investigate the correlative problems. Firstly the paper developed independently three dimensional unsteady parallel computational code-MpiTurbo based on Fortran 90 and MPI at Linux operating system. Then unsteady numerical simulation was carried out to investigate impacts of the factors, which included circumferential locations of hot streak and clocking positions of blade rows, on the thermal environment of a 1+1 counter-rotating turbine. The results clearly indicated that clocking positions of hot streak/blade row and blade row/blade row had great influence on the time-averaged temperature distribution of the third blade row. Therefore, it can be effective for improving thermal environment of turbine to optimize blade parameters and clocking positions. Lastly film cooling layout was designed by the repetitious steady simulation based on source term method. And the flow structure detail was given by the unsteady simulation.

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“…There are extensive experimental [Whitney et al, 1980, Schwab et al, 1983, Stabe et al, 1984, Butler et al, 1989, Sharma et al, 1992, Shang et al, 1995 and numerical [Rai and Dring, 1990, Krouthen and Giles, 1988, Takahashi and Ni, 1991, Shang and Epstein, 1996, Dorney et al, 2000 results for the influence of temperature non-uniformities on the flow and heat transfer in a conventional turbine. To the best knowledge of the authors, however, there are no data available in the open literature for the effect of in situ reheat on turbine-burners.…”

Section: Introductionmentioning

confidence: 99%