On the Performance of Gas Turbine Secondary Air Systems

Foley, Andrew

doi:10.1115/2001-gt-0199

Cited by 8 publications

(5 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A calculation of temperature at the bleed offtake(s) is required in order to calculate bleed enthalpy and work, and the effect of remixing the bleed air back into the main gas path. However, as bleed air is often used for downstream secondary systems such as bearing sealing, turbine blade cooling, or cabin pressure air [10], knowledge of the pressure of bleed air is also required. Pressure and temperature at the bleed point may be calculated using a simple assumption that it is equal to the compressor exit temperature and pressure.…”

Section: Identification Of Bleed Properties -Flow Pressure and Temperaturementioning

confidence: 99%

A method for modelling compressor bleed in gas turbine analysis software

Hackney

Nikolaidis

Pellegrini

2020

Applied Thermal Engineering

View full text Add to dashboard Cite

This is a PDF file of an article that has undergone enhancements after acceptance, such as the addition of a cover page and metadata, and formatting for readability, but it is not yet the definitive version of record. This version will undergo additional copyediting, typesetting and review before it is published in its final form, but we are providing this version to give early visibility of the article. Please note that, during the production process, errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain.

show abstract

Section: Identification Of Bleed Properties -Flow Pressure and Temperaturementioning

confidence: 99%

A method for modelling compressor bleed in gas turbine analysis software

Hackney

Nikolaidis

Pellegrini

2020

Applied Thermal Engineering

View full text Add to dashboard Cite

show abstract

“…The experimental data covers a wide range of nondimensional conditions with rotational Reynolds numbers from 3x10 6 to 3x10 7 and throughflow Reynolds numbers from 3x10 4 to 1x10 5 for a gap ratio of 0.1 and an exit gap ratio of 0.038. A full uncertainty analysis was carried out on the experimental rig and it was found that the standard variation in recorded torque was +/-0.346 N m (or +/-0.678 N m with a 95% confidence interval) at all rotational and throughflow Reynolds numbers.…”

Section: Equation (2)mentioning

confidence: 99%

“…For instance, a massive increase in secondary air system performance (e.g. 10%) may only increase the overall cycle efficiency by 0.15% [4]. As a result a full and complete understanding of these internal airflows is essential to increase cooling system effectiveness and hence progress gas-turbine design in the future.…”

Section: Introductionmentioning

confidence: 99%

Model Validation for a Shrouded Rotor-Stator System With Superposed Cooling and Static Protuberances

Pett

Coren

Childs

2007

Volume 6: Turbo Expo 2007, Parts a and B

View full text Add to dashboard Cite

This paper analyses numerical and experimental data gathered from a shrouded rotor-stator wheelspace supplied with a radial outflow of cooling air introduced along its central axis. Computational Fluid Dynamics (CFD) investigations into plain disc, roughened disc, roughened stator and stator protrusions were carried out and the results compared to previously gathered experimental data in order to validate the CFD code and improve confidence in its ability to model the given situations.Comparisons of cooling air flow enthalpy rises, torques required to drive the disc and one-sided moment coefficients for the disc have been made between the experimental and the computational models and agreement was obtained across the range of nondimensional numbers analysed. For the plain disc analyses this agreement was within 2% to 15% and was from 6% to 20% for the static protrusions on the stator. Results for the roughness on the rotor models corresponded closely with the experimental findings of previous authors. It was also confirmed that increasing roughness on the rotor increased moment coefficient and that increasing roughness from hydrodynamically smooth up to a roughness ratio of 1125 (corresponding to a roughness height of 0.2 mm) caused a doubling of torque at all rotational and throughflow Reynolds numbers. The same magnitude of roughness on stator was also found to double the torque experienced by the stationary casing but this only corresponded to a 5% increase in disc moment coefficient.

show abstract

“…Many scholars have modeled and analyzed the whole secondary air system, considering each of its elements as a "black box" and establishing the connections among them. The network of the secondary air system is drawn, and the conditions of each element during different phases are predicted using analysis codes (e.g., ESMS) [10][11][12]. However, unlike those simplified quasi-one-dimensional models, the flow within the compressor bleed system is strongly three-dimensional and the different parts interact with each other.…”

Section: Introductionmentioning

confidence: 99%

Effects of Geometry of Plenum Chamber on Losses in the Bleed System of an Axial Compressor

Shi

Kong

Jia

2022

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

To study how the geometry of the plenum chamber in the bleed system of an axial compressor influences the losses therein and to establish a theoretical loss model for this system, a 1.5-stage axial compressor with a bleed system is studied numerically by means of computational fluid dynamics (CFD). The results show that losses in the bleed system occur mainly in the axisymmetric bleed slot and plenum chamber, accounting for ca. 85% of the total loss. For a bleed system with a vertical axisymmetric slot, the loss is more sensitive to the radial height than to the axial width of the plenum chamber. A loss model for each part of the bleed system is established via theoretical analysis, and then, a model of the overall bleed system is established by combining these submodels. The predictions of the theoretical loss model agree well with the CFD results: the maximum prediction error for the coefficient of the stagnation pressure loss in the bleed system is −1.38%, and the average prediction error is −0.8%. This loss model can be used when designing the geometry of a bleed system.

show abstract

On the Performance of Gas Turbine Secondary Air Systems

Cited by 8 publications

References 0 publications

A method for modelling compressor bleed in gas turbine analysis software

A method for modelling compressor bleed in gas turbine analysis software

Model Validation for a Shrouded Rotor-Stator System With Superposed Cooling and Static Protuberances

Effects of Geometry of Plenum Chamber on Losses in the Bleed System of an Axial Compressor

Contact Info

Product

Resources

About