Application of a Fast Loosely Coupled Fluid/Solid Heat Transfer Method to the Transient Analysis of Low-Pressure-Turbine Disk Cavities

Altuna, Arnau; Chaquet, José M.; Corral, Roque; Gisbert, Fernando; Pastor, Guillermo

doi:10.1115/gt2013-95426

Cited by 8 publications

(4 citation statements)

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“…The objective of this subsection, and of the previous analyses, is to elucidate when the heat transfer at the wall can be computed using a quasi-steady approximation during a disk transient. Fully coupled fluid-solid transient analyses of realistic gas turbine cavities have been computed in the past (Ganine et al 2012;Altuna et al 2013).…”

Section: Evaluation Of Unsteady Effectsmentioning

confidence: 99%

“…The motivation for this simplification is associated to the simulation cost, which has given rise to the analysis of optimal strategies to minimise the cost of the coupling (Corral & Wang 2018). However the physical basis of this strong hypothesis has not been properly assessed for transient cavity flows (Altuna et al 2013;Chaquet et al 2015;Sun et al 2016). The work reported here reviews the order of magnitude of the characteristic times involved in this process, and presents numerical results for the first time of the thermal transient in a simplified rotor-stator cavity for engine representative non-dimensional parameters.…”

Section: Introductionmentioning

confidence: 99%

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On the transient behaviour of a laminar rotor–stator cavity

Corral

Romera

2018

J. Fluid Mech.

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The unsteady laminar flow between two large rotating disks when one of them is impulsively started is described using the von Kármán similarity analysis to reduce the solution of the Navier–Stokes equations to a set of ordinary differential equations. It is found that the transient phenomenon consists of three distinct phases. Firstly, the development of the Ekman boundary layer, where a quasi-steady Stewartson-type of flow is created. Secondly, angular momentum is initially diffused in the axial direction until the inward radial convection of angular momentum becomes dominating. Thirdly, a Batchelor flow is created once the Bödewadt boundary layer is developed and the entrainment of disk and stator boundary layers are balanced. The dependences of the characteristic dimensionless times on the Reynolds number based on the cavity gap for the second and third stages have been identified numerically and analytically. It is found that the diffusive part of the transient is bypassed if the flow, initially at rest, is perturbed with a small circumferential velocity. The flow and heat transfer transient during a ramp of finite duration has been computed numerically. The integral angular momentum and energy balances of the cavity have been performed in order to understand the energy and momentum budget of the cavity. It is concluded that the spin-up and the spin-down process of a rotor–stator cavity using a quasi-stationary approximation of the fluid, where the time derivatives are neglected, is questionable for realistic gas turbine applications. Finally, the self-similar solution is compared against two-dimensional axisymmetric, steady and unsteady, laminar simulations to assess the limitations and validity of the self-similar analysis. It has been identified that in a closed squared cavity the outer shroud modifies the physics of the transient, but the general conclusions drawn from the one-dimensional model are still valid.

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Section: Evaluation Of Unsteady Effectsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

On the transient behaviour of a laminar rotor–stator cavity

Corral

Romera

2018

J. Fluid Mech.

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“…The second method, the loosely coupled method, uses a special heat conduction program to solve structural heat transfer and a CFD program to solve flow. To simplify the implementation, the loosely coupled method between fluid and solid solvers is often adopted [6]. When the loosely coupled method is adopted, the convergence of calculation depends on the method of information exchange between the fluid regions and the solid regions.…”

Section: Introductionmentioning

confidence: 99%

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Chen

Jian

et al. 2023

Aerospace

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To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber, radiation heat transfer, heat conduction in the wall, heat transfer of coolant flow in the cooling channel, and gas film cooling in the thrust chamber wall. The numerical method used in each physical area, the data transfer method between each computing module, the strategy of data transfer on the coupling interface, the calculation process, and the convergence criterion are all introduced in detail. The calculation scheme was verified by analyzing a water-cooled nozzle. Then, the coupled heat transfer calculation was carried out for a liquid rocket engine using a propellant composed of unsymmetrical dimethylhydrazine and dinitrogen tetroxide. Two working conditions were analyzed: whether the gas film cooling was performed or not. The results showed that the algorithm successfully indicated the protective effect of the gas film on the wall surface, and the calculation results were reasonable. It played a guiding role for the coupled heat transfer of the liquid rocket engine using a composite cooling method.

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“…Owing to high computational costs earlier efforts were mostly limited to steady analyses at the component level [2,3,4,5]. Transient conjugate heat transfer analysis to capture heat flux and wall temperature distribution were carried out in [6,7,8,9,10,11]. In the majority of cases the literature reports a reasonable level of agreement with experimental data at both steady-state and transient operating conditions.…”

Section: Introductionmentioning

confidence: 99%

Transient Aero-Thermo-Mechanical Multidimensional Analysis of a High Pressure Turbine Assembly Through a Square Cycle

Ganine

Chew

Hills

et al. 2021

Journal of Engineering for Gas Turbines and Power

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Better understanding and more accurate prediction of heat transfer and cooling flows in aero engine components in steady and transient operating regimes are essential to modern engine designs aiming at reduced cooling air consumption and improved engine efficiencies. This paper presents a simplified coupled transient analysis methodology that allows assessment of the aerothermal and thermomechanical responses of engine components together with cooling air mass flow, pressure and temperature distributions in an automatic fully integrated way. This is achieved by assembling a fluid network with contribution of components of different geometrical dimensions coupled to each other through dimensionally heterogeneous interfaces. More accurate local flow conditions, heat transfer and structural displacement are resolved on a smaller area of interest with multidimensional surface coupled CFD/FE codes. Contributions of the whole engine air-system are predicted with a faster mono dimensional flow network code. Matching conditions at the common interfaces are enforced at each time step exactly by employing an efficient iterative scheme. The coupled simulation is performed on an industrial high pressure turbine disk component run through a square cycle. Predictions are compared against the available experimental data. The paper proves the reliability and performance of the multidimensional coupling technique in a realistic industrial setting. The results underline the importance of including more physical details into transient thermal modelling of turbine engine components.

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Application of a Fast Loosely Coupled Fluid/Solid Heat Transfer Method to the Transient Analysis of Low-Pressure-Turbine Disk Cavities

Cited by 8 publications

References 0 publications

On the transient behaviour of a laminar rotor–stator cavity

On the transient behaviour of a laminar rotor–stator cavity

A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine

Transient Aero-Thermo-Mechanical Multidimensional Analysis of a High Pressure Turbine Assembly Through a Square Cycle

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