Conjugate Heat Transfer Analysis of Convection-cooled Turbine Vanes Using γ-Reθ Transition Model

Lin, Gang; Kusterer, Karsten; Ayed, A. Haj; Bohn, Dieter; Sugimoto, T.

doi:10.38036/jgpp.6.3_9

Cited by 12 publications

(4 citation statements)

References 16 publications

(16 reference statements)

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“…model near walls in order to have a good prediction of the boundary layer and k-" model for the other parts of flow. As reported by Lin et al, 19 the SST turbulence model had the best results for the conjugate heat calculation.…”

Section: Numerical Approachsupporting

confidence: 57%

Performance improvement of a high pressure ratio centrifugal compressor by integrated cooling

Moosania

Zheng

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Centrifugal compressors with high pressure ratio have been widely used in small gas turbines, industrial compressors and turbochargers. High mechanical stress and high temperature of the impeller and large compression power required are the key factors that limit the pressure ratio achieved by centrifugal compressors. Cooling is an effective way to reduce the required compression power and the impeller temperature and it is widely used in gas turbines and industrial compressors. In this work, a cooling method named integrated cooling was employed in a high pressure ratio centrifugal compressor. The effects of the integrated cooling on the compressor performance were studied by three-dimensional steady simulation with conjugate heat transfer method using ANSYS CFX commercial solver. It is found that integrated cooling is capable of improving the compressor performance with respect to pressure ratio, efficiency, compression power as well as the impeller maximum temperature. With a cooling temperature of 300 K, the pressure ratio increased by 11.0% and efficiency by about 2.44% at the design condition. Besides, the maximum impeller temperature decreased by about 67 K. This considerable improvement of the compressor performance justifies the integrated cooling, which helps to advance the design of high pressure ratio centrifugal compressors.

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Section: Numerical Approachsupporting

confidence: 57%

Performance improvement of a high pressure ratio centrifugal compressor by integrated cooling

Moosania

Zheng

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The primary cause of the discrepancy on the suction surface of the leading edge is the due to the limitation of the Spalart-Allmaras turbulence model. This model is not well suited for modelling transitional flow and transitional models can be used to better match the experiment (Hongjun et al 2013;Hao et al 2014;Lin et al 2014).…”

Section: Baseline Analysismentioning

confidence: 99%

Discrete adjoint for coupled conjugate heat transfer

Imam-Lawal

Verstraete

Müller

2023

Struct Multidisc Optim

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The typical method to solve multi-physics problems such as Conjugate Heat Transfer (CHT) is the partitioned approach which couples separate solvers through boundary conditions. Effective gradient-based optimisation of partitioned CHT problems requires the adjoint of the coupling to maintain the efficiency of the original multi-physics coupling, which is a significant challenge. The use of automatic differentiation (AD) has the potential to ease this burden and leads to generic gradient computation methods. In this paper, we present how to automate the generation of adjoint fluid and solid solvers for a CHT adjoint using Automatic Differentiation (AD). The derivation of the adjoint of the loose coupling algorithms is shown for three fixed-point coupling algorithms. Application of the coupled adjoint algorithm is shown to two CHT optimisation benchmark cases for inverse design and shape optimisation. The results demonstrate that Robin-based coupling algorithms have faster runtimes and are an attractive option for CHT optimisation problems.

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“…This code is appropriate for turbomachinery analysis. For example, Lin et al (5) used the Star-CCM+ analysis for the conjugate analysis of heat transfer to a gas turbine vane. The k − ω SST turbulence model was used by by Ameri et al (6) to predict turbine blade tip region clearance flows and heat transfer.…”

Section: Improved Efficiency For Shrouded Rotorsmentioning

confidence: 99%

Shrouded CMC Rotor Blades for High Pressure Turbine Applications

Boyle

Agricola

Parikh

et al. 2018

Volume 2B: Turbomachinery

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The density of Ceramic Matrix Composite (CMC) materials is approximately 1/3 the density of metals currently used for High Pressure Turbine (HPT) blades. A lower density, and consequently lower centrifugal stresses, increases the feasibility of shrouding HPT blades. Shrouding HPT blades improves aerodynamic efficiency, especially for low aspect ratio turbine blades. This paper explores aerodynamic and structural issues associated with shrouding HPT rotor blades. Detailed Navier-Stokes analysis of a rotor blade showed that shrouding improved blade row aerodynamic efficiency by 1.3%, when the clearance was 2% of the blade span. Recessed casings were used. Without a shroud the depth of the recess equaled the clearance. With a shroud the recess depth increased by the shroud thickness, which included a knife seal. There was good agreement between the predicted stage efficiency for the unshrouded blades and the experimentally measured efficiency. Structural analysis showed a strong interaction between stresses in the shroud and peak stresses at the hub of the blade. A thin shroud of uniform thickness only moderately increased maximum blade stress, but there were very high stresses in the shroud itself. Increasing shroud thickness reduced stresses in the shroud, but increased blade stresses near the hub. A single knife seal added to the thin shroud noticeably decreased maximum shroud stress, without increasing maximum blade stress. Maximum stresses due to pressure loads and combined pressure and centrifugal loads were nearly the same as the maximum stresses for individual pressure or centrifugal loads. Stresses due to a 100K temperature difference across the blade walls were much lower than centrifugal or pressure load stresses.

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Conjugate Heat Transfer Analysis of Convection-cooled Turbine Vanes Using γ-Reθ Transition Model

Cited by 12 publications

References 16 publications

Performance improvement of a high pressure ratio centrifugal compressor by integrated cooling

Performance improvement of a high pressure ratio centrifugal compressor by integrated cooling

Discrete adjoint for coupled conjugate heat transfer

Shrouded CMC Rotor Blades for High Pressure Turbine Applications

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