Three-Dimensional Navier-Stokes Analysis of a Two-Stage Gas Turbine

Arnone, Andrea; Benvenuti, Erio

doi:10.1115/94-gt-088

Cited by 20 publications

(12 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…If one stator and two rotors have the same pitch angle, calculation errors during the numerical analysis can be minimized. As such, the number of blades was adjusted using a domain scaling method to create two rotors that correspond to the pitch of one stator in each stage [16]. In a state where the number of first stage rotors and the solidity of each blade are fixed, each chord length of the first stage stator (S1), second-stage stator (S2), and the rotor (R2) were magnified by 46/38, 48/38, and 70/76, respectively.…”

Section: Numerical Model and Gridmentioning

confidence: 99%

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Choi

Ryu

2018

Energies

View full text Add to dashboard Cite

Combined cycle power plants (CCPPs) are becoming more important as the global demand for electrical power increases. The power and efficiency of CCPPs are directly affected by the performance and thermal efficiency of the gas turbines. This study is the first unsteady numerical study that comprehensively considers axial gap (AG) in the first-stage stator and first-stage rotor (R1) and hot streaks in the combustor outlet throughout an entire two-stage turbine, as these factors affect the aerodynamic performance of the turbine. To resolve the three-dimensional unsteady-state compressible flow, an unsteady Reynolds-averaged Navier-Stokes (RANS) equation was used to calculate a k − ω SST γ turbulence model. The AG distance d was set as 80% (case 1) and 120% (case 3) for the design value case 2 (13 mm or d/Cs 1 = 0.307) in a GE-E 3 gas turbine model. Changes in the AG affect the overall flow field characteristics and efficiency. If AG decreases, the time-averaged maximum temperature and pressure of R1 exhibit differences of approximately 3 K and 400 Pa, respectively. In addition, the low-temperature zone around the hub and tip regions of R1 and second-stage rotor (R2) on the suction side becomes smaller owing to a secondary flow and the area-averaged surface temperature increases. The area-averaged heat flux of the blade surface increases by a maximum of 10.6% at the second-stage stator and 2.8% at R2 as the AG decreases. The total-to-total efficiencies of the overall turbine increase by 0.306% and 0.295% when the AG decreases.

show abstract

Section: Numerical Model and Gridmentioning

confidence: 99%

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Choi

Ryu

2018

Energies

View full text Add to dashboard Cite

show abstract

“…Also an important disagreement on the peak efficiency position has to be noticed. Such a situation is known to be a consequence of spurious shock system reflections at the interface boundary (Amone and Benvenuti, 1994). If the axial gap is increased to 1.25 of the design value, no sensible reflections are experienced and the computed characteristic is very similar to the unsteady one.…”

Section: Steady Ditch-averaged Analysismentioning

confidence: 99%

“…Modern state-of-the-art turbine and compressor stages work in transonic regimes and stator and rotors an stacked very close to each other. If inlet and outlet boundaries are located at short distances from the blade rows, the use of the one-dimensional characteristic boundary treatment described above may result in undesired reflections of shock waves (Amone and Benvenuti, 1994). Moreover, the pitch-averaging process takes place close to the blade passage and, depending on the avenging procedure, the conservation of mass or momentum or energy can be poor if the flow exhibits strong gradients.…”

Section: Boundary Conditionsmentioning

confidence: 99%

IGV-Rotor Interaction Analysis in a Transonic Compressor Using the Navier-Stokes Equations

Arnone

Pacciani²

1996

Volume 1: Turbomachinery

Self Cite

View full text Add to dashboard Cite

A recently developed, time-accurate multigrid viscous solver has been extended to handle quasi-three-dimensional effects and applied to the first stage of a modern transonic compressor. Interest is focused on the inlet guide vane (IGV):rotor interaction where strong sources of unsteadiness are to be expected. Several calculations have been performed to predict the stage operating characteristics. Flow structures at various mass flow rates, from choke to near stall, are presented and discussed. Comparisons between unsteady and steady pitch-averaged results are also included in order to obtain indications about the capabilities of steady, multi-row analyses.

show abstract

“…This paper examines just how far the now widely accepted mixingplane model* [11][12][13] ), is capable of accurately predicting the flowfield within an embedded blade-row. What makes this study original is that for the first time the method is being compared with a self-consistent dataset that includes detailed measurements taken through several blade-rows, with data from both the stationary and rotor-relative frames of reference.…”

Section: Nomenclature C Pmentioning

confidence: 99%

Experimental audit of the mixing-plane approach to turbomachinery analysis and a review of alternative multi-row techniques

Lockwood¹,

Ivey²,

Wells³

2000

Aeronaut. j.

View full text Add to dashboard Cite

Detailed numerical comparisons of pressure and flow angle measurements made in stage three of a four-stage, large scale, low speed, axial compressor are presented. The measurements are in both the rotating and stationary frame and were obtained as part of a BRITE/EURAM collaborative study of cantilevered and shrouded-stator compressor configurations. The numerical analysis is 3D, considers three blade rows simultaneously and incorporates multiple row effects by use of a conservative mixing-plane model allowing circumferential variation at the mixing plane. The paper discusses the early results of a study sponsored by Alstom Gas Turbines to examine steady-state, multiple blade-row modelling techniques. Growth in the endwall flow region due to multi-row effects is revealed from both the numerical and experimental results. The numerical simulation is conducted without altering blade gap spacings to assist numerical stability; the axial gap is increasingly being seen as a critical performance parameter for multiple row analysis. The limitations inherent in an approach using mixing-planes are presented and a review of alternative, more rigourous, treatments of these effects is then discussed. These treatments attempt to retain the unsteady flow structure in a steady-state model by the derivation of so-called deterministic stresses.

show abstract

Three-Dimensional Navier-Stokes Analysis of a Two-Stage Gas Turbine

Cited by 20 publications

References 15 publications

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

Numerical Study of the Axial Gap and Hot Streak Effects on Thermal and Flow Characteristics in Two-Stage High Pressure Gas Turbine

IGV-Rotor Interaction Analysis in a Transonic Compressor Using the Navier-Stokes Equations

Experimental audit of the mixing-plane approach to turbomachinery analysis and a review of alternative multi-row techniques

Contact Info

Product

Resources

About