Heat transfer to He I and He II in pulsed thermal loading

1981 ◽  
Vol 40 (3) ◽  
pp. 235-238
Author(s):  
A. M. Arkharov ◽  
A. I. Ageev ◽  
V. I. Pryanichnikov ◽  
N. B. Rubin
Keyword(s):  
Heat Transfer ◽  
Thermal Loading

Analysis of a Virtual Prototype First-Stage Rotor Blade Using Integrated Computer-Based Design Tools

2006 ◽  
Author(s):  
Michel Arnal ◽  
Christian Precht ◽  
Thomas Sprunk ◽  
Tobias Danninger ◽  
John Stokes
Keyword(s):  
Heat Transfer ◽  
Gas Flow ◽  
Thermal Loading ◽  
Cfd Simulation ◽  
Three Dimensional ◽  
Life Assessment ◽  
Element Analysis ◽  
Pressure Losses ◽  
Cooling Channels ◽  
Internally Cooled

The present paper outlines a practical methodology for improved virtual prototyping, using as an example, the recently re-engineered, internally-cooled 1st stage blade of a 40 MW industrial gas turbine. Using the full 3-D CAD model of the blade, a CFD simulation that includes the hot gas flow around the blade, conjugate heat transfer from the fluid to the solid at the blade surface, heat conduction through the solid, and the coolant flow in the plenum is performed. The pressure losses through and heat transfer to the cooling channels inside the airfoil are captured with a 1-D code and the 1-D results are linked to the three-dimensional CFD analysis. The resultant three-dimensional temperature distribution through the blade provides the required thermal loading for the subsequent structural finite element analysis. The results of this analysis include the thermo-mechanical stress distribution, which is the basis for blade life assessment.

Heat Transfer in Periodically Laminated Structures – Third Type Boundary Conditions

2020 ◽  
pp. 2041011
Author(s):  
Ewelina Pazera
Keyword(s):  
Heat Transfer ◽  
Boundary Conditions ◽  
Thermal Loading ◽  
Laminated Composite ◽  
Homogeneous Layer ◽  
Heat Transfer Phenomenon ◽  
The Finite Difference Method ◽  
Type Boundary ◽  
Robin Boundary ◽  
Laminated Structures

This work is about a heat transfer phenomenon in relation to the periodically laminated composite. The specific type of thermal loading, analyzed in this paper, require formulation of Robin boundary conditions. To consider a layered structure of analyzed composite, the tolerance averaging technique is used. This method allows to take into account a thickness of the layers and obtain the equations with continuous coefficients. To solve these equations, the finite difference method is used, because an analytical solution is not available in this case (in contrast to the analogous issue in relation to a homogeneous layer).

Numerical 3-D Conjugated Heat Transfer Simulation of a First Inter-Stage Internal Cooled Thermal Barrier Coated Gas Turbine Bucket

2007 ◽  
Author(s):  
Alejandro Herna´ndez Rossette ◽  
Zdzislaw Mazur C. ◽  
Jesu´s Cordero Guridi ◽  
Eric Chumacero Polanco
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Thermal Loading ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Thermal Barrier ◽  
Cfd Simulations ◽  
Temperature Changes ◽  
Heat Transfer Simulation ◽  
Conjugated Heat Transfer

As a gas turbine entry temperature (TET) increases, thermal loading on first stage blades increases too and therefore, a variety of cooling techniques and thermal barrier coatings (TBCs) are used to maintain the blade temperature within the acceptable limits. In this work a multi-block three dimensional Navier-Stokes commercial turbomachinery oriented CFD-code has been used to compute steady state conjugated heat transfer (CHT) on the blade suction and pressure coated sides of a rotating first inter-stage (nozzle and bucket) with cooling holes of a 60 MW Gas turbine. A Spallart Allmaras model was used for modeling the turbulence. Convection and radiation were modeled for a super alloy blade with and without TBC. The CFD simulations were configured with a mesh domain of nozzle and bucket inter-stage in order to predict the fluid parameters at inlet and outlet of bucket for validate with turbine inter-stage parameter data test of gas turbine manufacturer. The effects of blade surface temperature changes were simulated with both configurations coated and uncoated blades.

Influence of a Variable in Time Heat Transfer Coefficient on Stresses in Model of Power Plant Components

2013 ◽  
Author(s):  
Jerzy Okrajni ◽  
Mariusz Twardawa
Keyword(s):  
Heat Transfer ◽  
Power Plant ◽  
Mechanical Behaviour ◽  
Power Plants ◽  
Thermal Loading ◽  
Computer Modelling ◽  
Temperature Fields ◽  
Fluid Medium ◽  
Stress Changes ◽  
Plant Components

The paper discusses the issue of modelling of strains and stresses resulting from heating and cooling processes of components in power plants. The main purpose of the work is to determine the mechanical behaviour of power plant components operating under mechanical and thermal loading. Finite element method (FEM) has been used to evaluate the temperature and stresses changes in components as a function of time. Temperature fields in the components of power plants are dependent, among parameters, on variable heat-transfer conditions between components and the fluid medium, which may change its condition, flowing inside them. For this reason, evaluation of the temperature field and the consequent stress fields requires the use of heat-transfer coefficients as time-dependent variables and techniques for determining appropriate values for these coefficients should be used. The methodology of combining computer modelling of the temperature fields with its measurements performed at selected points of the pipelines may be used in this case. The graphs of stress changes as a function of time have been determined for the chosen plant components. The influence of the heat transfer conditions on the temperature fields and mechanical behaviour of components have been discussed.

Use of a CFD-Tool for Assessment of the Reactor Pressure Vessel Integrity in Pressurised Thermal Shock Conditions: Thermal-Hydraulic Studies of a Safety Injection in a PWR Plant — Methodology and Present Limitation

2007 ◽  
Author(s):  
A. Martin ◽  
S. Bosse ◽  
F. Lestang
Keyword(s):  
Heat Transfer ◽  
Thermal Shock ◽  
Thermal Loading ◽  
Development Program ◽  
Pressure Vessels ◽  
Surveillance Program ◽  
Fluid Temperature ◽  
Two Phase ◽  
Safety Margins ◽  
Reactor Pressure

Integrity evaluation methods for nuclear Reactor Pressure Vessels (RPVs) under Pressurised Thermal Shock (PTS) loading are applied by French Utility. They are based on the analysis of the behaviour of cracks under PTS loading conditions due to the emergency cooling during PTS transient like SBLOCA. This paper explains the Research and Development program started at Electricite´ De France about the cooling phenomena of a PWR vessel after a Pressurised Thermal Shock. The numerical results are obtained with the E.D.F ThermalHydraulic code (Code_Saturne) coupled with the thermal-solid code SYRTHES to take into account the conjugate heat transfer on the cooling of the vessel. We first explain the global methodology with a progress report on the state of the art of the tools available to simulate the different scenari displayed within the frame of the plant life project in order to reassess the integrity of the RPV, taking into account the evolution of some input data, such as the new value of end of life (EOL) fluence, the feedback results of surveillance program and the evolution of the functional requirements. The main results are presented and are related to the evaluation of the RPV integrity during a Small Break Loss Of Coolant Accident transient for 900 and 1300 MWe nuclear plant. On the whole, the main purpose of the numerical CFD studies is to accurately estimate the distribution of fluid temperature in the down comer and the heat transfer coefficients on the inner RPV surface for a fracture mechanics computation which will subsequently assess the associated RPV safety margins. In a second time, a new analysis is performed to assess an accurate temperature distribution in the RPV. Indeed, from a physical phenomena point of view, the EDF thermalhydraulic tool Code_Saturne is now qualified in order to assess single phase transient but in the case where the cold legs are partially filled with steam, it becomes a two-phase problem and new important effects occur, such as condensation due to the emergency core cooling injections of sub-cooled water. Thus, an advanced prediction of RPV thermal loading during these transients requires sophisticated two-phase, local scale, 3D codes. In that purpose, a program has been set up to extend the capabilities of the Neptune_CFD two-phase solver which is the tool able to solve two phase flow configuration. In a same time, A simplified approach has showed that for a type of transient weakly uncovered, a free surface calculation was sufficient to respect the necessary criteria of safety. A Qualification study was carried out on the Hybiscus experimental E.D.F facility, representing a cold leg with ECC injection and a third down comer. Temperature profiles have been compared and are presented and analysed here, showing encouraging results.

Influence of High Rotational Speeds on Heat Transfer and Oil Film Thickness in Aero-Engine Bearing Chambers

1994 ◽  
Vol 116 (2) ◽  
pp. 395-401 ◽  
Author(s):  
S. Wittig ◽  
A. Glahn ◽  
J. Himmelsbach
Keyword(s):  
Heat Transfer ◽  
Film Thickness ◽  
Thermal Loading ◽  
Local Heat Transfer ◽  
Local Heat ◽  
Test Facility ◽  
High Rotational Speed ◽  
Oil Film ◽  
Aero Engine

Increasing the thermal loading of bearing chambers in modern aero-engines requires advanced techniques for the determination of heat transfer characteristics. In the present study, film thickness and heat transfer measurements have been carried out for the complex two-phase oil/air flow in bearing chambers. In order to ensure real engine conditions, a new test facility has been built up, designed for rotational speeds up to n = 16,000 rpm and maximum flow temperatures of Tmax = 473 K. Sealing air and lubrication oil flow can be varied nearly in the whole range of aero-engine applications. Special interest is directed toward the development of an ultrasonic oil film thickness measuring technique, which can be used without any reaction on the flow inside the chamber. The determination of local heat transfer at the bearing chamber housing is based on a well-known temperature gradient method using surface temperature measurements and a finite element code to determine temperature distributions within the bearing chamber housing. The influence of high rotational speed on the local heat transfer and the oil film thickness is discussed.

Aerothermal Analysis of a Turbine With Rim Seal Cavity

2014 ◽  
Author(s):  
Huoxing Liu ◽  
Yuge An ◽  
Zhengping Zou
Keyword(s):  
Heat Transfer ◽  
Thermal Conduction ◽  
Thermal Loading ◽  
Leading Edge ◽  
Load Prediction ◽  
Blade Loading ◽  
Ansys Cfx ◽  
Annulus Flow ◽  
Tangential Momentum ◽  
Commercial Solver

This study presents the results of the aerothermal analysis of an axial turbine with rim seal cavity using conjugate heat transfer computation (CHT). The CHT computations were performed for a two-stage turbine with stator well cavity at the sealing flow rates between 0–2% of the main annulus flow utilizing the commercial solver ANSYS CFX. The results were compared with that of conventional uncoupled approaches in which a heat transfer coefficient is first derived from CFD solutions and then taken as boundary condition for a thermal conduction analysis of the solid domains. As it turns out, for the thermal load prediction, the global results obtained by CHT and uncoupled computations were similar, while with the increase of sealing flow rate remarkable differences emerged. In addition, the sealing flow significantly affects the thermal loading of the blade and disk as well as the strength of the secondary vortex. A negative incidence at the downstream rotor leading edge was observed along with the changing of blade loading due to the low tangential momentum cavity egress flow.

The Effects of Thermal Loading on the Mechanical Properties of Interfaces of Dissimilar Materials by Nanoindentation Simulations

2011 ◽  
Vol 133 (2) ◽  
Author(s):  
Ningbo Liao ◽  
Ping Yang ◽  
Miao Zhang ◽  
Wei Xue
Keyword(s):  
Heat Transfer ◽  
Mechanical Properties ◽  
Molecular Dynamics ◽  
Thermal Cycling ◽  
Thermal Loading ◽  
Mechanical Test ◽  
Dissimilar Materials ◽  
Md Simulations ◽  
Test Models ◽  
Critical Consideration

Heat transfer across the interfaces of dissimilar materials is a critical consideration in a wide variety of scientific and engineering applications. In this paper, molecular dynamics (MD) simulations are conducted to investigate the effects of thermal loading on mechanical properties of Al–Cu and Cr–Cu interfaces. The mechanical properties are investigated by MD simulations of nanoindentation. Both the results of MD simulations and experiments show the Young’s modulus decrease after thermal cycling, and the Cr–Cu interface is more sensitive to the thermal loading than the Al–Cu interface. The thermal loading and mechanical test models proposed here can be used to evaluate interfacial properties under the effects of heat transferring.

Analysis on the Effect of a Non-Uniform Inlet Profile on Heat Transfer and Fluid Flow in Turbine Stages

2010 ◽  
Author(s):  
Salvadori Simone ◽  
Francesco Montomoli ◽  
Francesco Martelli ◽  
Kam S. Chana ◽  
Imran Qureshi ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Temperature Profile ◽  
Thermal Load ◽  
Thermal Loading ◽  
Radial Profile ◽  
Experimental Studies ◽  
Test Facility ◽  
Inlet Temperature ◽  
Inlet Conditions ◽  
Hot Streak

This paper presents an investigation of the aerothermal performance of a modern unshrouded high pressure (HP) aeroengine turbine subject to non-uniform inlet temperature profile. The turbine used for the study was the MT1 turbine installed in the QinetiQ Turbine Test Facility (TTF) based in Farnborough (UK). The MT1 turbine is a full scale transonic HP turbine, and is operated in the test facility at the correct non-dimensional conditions for aerodynamics and heat transfer. Datum experiments of aero-thermal performance were conducted with uniform inlet conditions. Experiments with nonuniform inlet temperature were conducted with a temperature profile that had a non-uniformity in the radial direction defined by (Tmax−Tmin)/T = 0.355, and a non-uniformity in the circumferential direction defined by (Tmax−Tmin)/T = 0.14. This corresponds to an extreme point in the engine cycle, in an engine where the non-uniformity is dominated by the radial distribution. Accurate experimental area surveys of the turbine inlet and exit flows were conducted, and detailed heat transfer measurements were obtained on the blade surfaces and end-walls. These results are analysed with the unsteady numerical data obtained using the in-house HybFlow code developed at the University of Firenze. Two particular aspects are highlighted in the discussion: prediction confidence for state of the art computational fluid dynamics (CFD) and impact of real conditions on stator-rotor thermal loading. The efficiency value obtained with the numerical analysis is compared with the experimental data and a 0.8% difference is found and discussed. A study of the flow field influence on the blade thermal load has also been detailed. It is shown that the hot streak migration mainly affects the rotor pressure side from 20% to 70% of the span, where the Nusselt number increases by a factor of 60% with respect to the uniform case. Furthermore, in this work it has been found that a nonuniform temperature distribution is beneficial for the rotor tip, contrary to the results found in the open literature. Although the hot streak is affected by the pressure gradient across the tip gap, the radial profile (which dominates the temperature profile being considered) is not fully mixed out in passing through the HP stage, and contributes significantly to cooling the turbine casing. A design approach not taking into account these effects will underestimate to rotor life near the tip and the thermal load at mid-span. The temperature profile that has been used in both the experiments and CFD is the first simulation of an extreme cycle point (more than twice the magnitude of distortion all previous experimental studies): it represents an engine-take-off condition combined with the full combustor cooling. The research was part of the EU funded TATEF2 (Turbine Aero-Thermal External Flows 2) programme.

Integration Scheme for Elastic Deformation and Stresses

1999 ◽  
Vol 66 (4) ◽  
pp. 978-985 ◽  
Author(s):  
S. L. Lee ◽  
C. R. Ou
Keyword(s):  
Heat Transfer ◽  
Finite Difference ◽  
Thermal Loading ◽  
Dirichlet Boundary ◽  
Integration Scheme ◽  
Linear Deformation ◽  
Interface Zone ◽  
Elastic Bodies ◽  
Difference Type ◽  
Grid Points

The integration scheme is proposed in this paper to solve linear deformation and stresses for elastic bodies. The discretized equations are of the finite difference type such that all of the advantages in the use of a finite difference scheme are preserved. In addition, the boundary traction can be easily converted into Dirichlet boundary condition for the displacement equations without recourse to fictitious points. Three examples are illustrated in this study to examine the performances of the integration scheme. In the case of thermal loading, the integration scheme is seen to provide solution with six-place accuracy while the finite element and the boundary element solutions possess only two- to three-place accuracy at essentially the same number of grid points. A similar situation is believed to exist also in the case of pure mechanical loading, although no exact solution is available for comparison. For a square bimaterial under a thermal loading without boundary traction, the integration scheme is found to successfully predict the existence of the interface zone. Due to its simplicity and efficiency, the integration scheme is expected to have good performance for solid mechanical problems, especially when coupled with heat transfer and fluid flow inside and outside the solid.

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