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

2013 ◽  
Author(s):  
Arnau Altuna ◽  
Jose M. Chaquet ◽  
Roque Corral ◽  
Fernando Gisbert ◽  
Guillermo Pastor
Keyword(s):  
Graphics Processing Units ◽  
Axisymmetric Flow ◽  
Low Pressure ◽  
Loosely Coupled ◽  
Low Pressure Turbine ◽  
Transfer Method ◽  
Turbine Design ◽  
Graphics Processing ◽  
Coupled Solution ◽  
Fully Coupled

A transient aero-thermal analysis of the disk cavities of an aero-engine LPT (Low Pressure Turbine) is presented. The full simulation includes a 2D thermal model of the solid parts combined with an axisymmetric flow model of six separate cavities interconnected through inlet and outlet boundaries. Computing elapsed time is significantly reduced by using a cluster of GPUs (Graphics Processing Units) making this approach compatible with turbine design time-frames. The problem of flow reversal that takes place in some of the cavity boundaries along the transient flight cycle is addressed in detail. The fully coupled numerical solution is validated against engine data and compared as well against an uncoupled simulation. It is shown that the coupled solution outperforms the uncoupled one in terms of accuracy, since it removes some hypotheses inherent to the uncoupled approach. It is believed that this is the first time that GPUs have been used to solve a fully coupled fluid/solid thermal problem of industrial interest for the gas turbine community.

A Loosely Coupled Fluid/Solid Heat Transfer Method for Disc Cavities Including Mixing Planes and a Combination of 2D and 3D Cavities

2015 ◽  
Author(s):  
Jose M. Chaquet ◽  
Roque Corral ◽  
Fernando Gisbert ◽  
Guillermo Pastor
Keyword(s):  
Heat Transfer ◽  
Graphics Processing Units ◽  
Three Dimensional ◽  
Coupled Model ◽  
Heat Transfer Analysis ◽  
Plane Boundary ◽  
Loosely Coupled ◽  
Transfer Method ◽  
Graphics Processing ◽  
2D And 3D

The effect of mixing plane boundary condition in conjugate heat transfer analysis is studied. The vehicle is a 1.5 stage warm turbine rig solved using a loosely coupled fluid/solid heat transfer method. To reduce the elapsed time, two and three dimensional CFD cavities are solved simultaneously in a Graphics Processing Units (GPU) cluster. The experimental data are compared against a coupled model with mixing plane distributions obtained from an adiabatic case. A moderate influence of the mixing plane on the results is observed, with non-dimensional temperature differences around 2% in some locations.

Comparing Human Driven and Automatic Blade Row Aerodynamic Designs

2017 ◽  
Author(s):  
Ricardo Puente ◽  
Roque Corral ◽  
Jorge Parra
Keyword(s):  
Graphics Processing Units ◽  
Flow Analysis ◽  
Design Environment ◽  
Low Pressure Turbine ◽  
Acceptable Quality ◽  
Turbine Vanes ◽  
Gradient Based ◽  
Graphics Processing ◽  
Short Time ◽  
Turbomachinery Design

In this paper a fast automatic design environment is developed, making use of a well established and validated turbomachinery design software system for geometry generation and flow analysis. The design is updated via a gradient based algorithm, where gradients are obtained via the adjoint method. The computational advantages of Graphics Processing Units are used to accelerate the mesh generation and flow analysis stages. The capabilities of the system are illustrated by automatically generating two Low Pressure Turbine vanes, and comparing them to the ones arrived at by a human designer, respecting the same explicit design criteria. The quality of the automatically designed airfoils is assessed against the human generated ones, and insight on the influence of implicit criteria is extracted. It is concluded that acceptable quality geometries can be designed automatically in a short time. For instance, the automatic procedure takes of the order of two days for an equivalent human driven case, where the designer took of the order of two weeks.

Verification of the Vibration Amplitude Prediction of Self-Excited LPT Rotor Blades Using a Fully Coupled Time-Domain Non-Linear Method and Experimental Data

2008 ◽  
Author(s):  
Roque Corral ◽  
Juan Manuel Gallardo
Keyword(s):  
Experimental Data ◽  
Dry Friction ◽  
Vibration Amplitude ◽  
Low Pressure ◽  
Rotor Blades ◽  
Navier Stokes ◽  
Disk Model ◽  
Low Pressure Turbine ◽  
Non Linear ◽  
Fully Coupled

The vibration level of aerodynamically unstable low-pressure-turbine rotor blades has been assessed for the first time using two-different approaches. Both methods assume that the aerodynamic forcing is due solely to the self-excitation of the airfoil and that the vibration amplitude is saturated due to the non-linearity associated to the fir-tree dry friction, which is modeled using a simplified approach. To compensate for the limitations of the friction model several hypotheses need to be done, among them, the geometric similarity of the different configurations and that the aspect ratio of the rotor blades is high. The first approach, which is novel, assumes that the vibration amplitude is small enough and the unsteady aerodynamics associated to the airfoil motion may be computed using a frequency domain linearized Navier-Stokes solver. The vibration amplitude is obtained posing the energy balance between the energy exerted by the most unstable aerodynamic mode and the energy dissipated by dry friction. The second approach time marches simultaneously the Reynolds-Average Navier Stokes equations and a simple mass-spring non-linear model consistent with the mechanical model used in the first approach. This fully coupled non-linear, both in the aerodynamic and structural sides, flutter analysis is considered unique in its kind. It is demonstrated by means of a simplified, but consistent with typical low-pressure-turbine bladed-disk, model that both methods are equivalent. The first approach has been applied to several bladed-disks and the comparison with experimental data is good in overall.

Aerodynamic Design of a New Five Stage Low Pressure Turbine for the Rolls Royce Trent 500 Turbofan

2001 ◽  
Author(s):  
I. Ulizar ◽  
P. González
Keyword(s):  
Low Pressure ◽  
Previous Experience ◽  
Aerodynamic Design ◽  
Design Work ◽  
Cost Performance ◽  
Detailed Design ◽  
Low Pressure Turbine ◽  
Lp Turbine ◽  
The Moment ◽  
Turbine Design

Almost a decade ago, ITP (Industria de Turbo Propulsores, S.A.) started to participate in Low Pressure turbine design supported by Rolls-Royce. The Trent 500 LP turbine aerodynamic design is the most challenging and extensive design work carried out to the moment. The Trent 500 is part of the Rolls Royce Trent family. It has been designed to enter in service in the Airbus 340-600. This engine has very aggressive targets in terms of cost, performance, weight and noise. An optimization process was carried out during the preliminary and detailed design phases to accomplish these targets. This paper describes the most outstanding characteristics of the LP turbine, how the previous experience and Research and Technology results have been employed in this design and also some of the new advanced features, e.g. the introduction of spoon aerofoils.

Low Pressure Turbine Design for Rolls-Royce Trent 900 Turbofan

2006 ◽  
Author(s):  
Paloma Gonza´lez ◽  
Mikel Lantero ◽  
Victor Olabarria
Keyword(s):  
Revenue Sharing ◽  
Low Pressure ◽  
Design Team ◽  
Design Phase ◽  
Low Pressure Turbine ◽  
Conceptual Design Phase ◽  
Key Characteristics ◽  
The World ◽  
Lp Turbine ◽  
Turbine Design

The Trent 900 engine is part of the Rolls-Royce Trent family, designed to enter into service in the Airbus 380, the largest commercial aeroplane in the world. The LP turbine design was performed in Spain by ITP. Since 1997 ITP has been involved in the Rolls-Royce Trent low pressure turbine design. In the Trent 900, ITP is one of the risk and revenue sharing partners of the project. The design team participated extensively in the low pressure turbine since the conceptual design phase to the engine certification that took place in October 2004 and it will continue through aeroplane civil operation. The aim of this paper is to describe some of the most key characteristics of the LP turbine design, mainly focused on the aerodynamics; The LP turbine concept will be shown, the new aerodynamic features described and how they are supported by former experimental data.

Highly Loaded Low-Pressure Turbine: Design, Numerical, and Experimental Analysis

2016 ◽  
Vol 32 (1) ◽  
pp. 142-152 ◽  
Author(s):  
J. T. Schmitz ◽  
E. Perez ◽  
S. C. Morris ◽  
T. C. Corke ◽  
J. P. Clark ◽  
...  
Keyword(s):  
Experimental Analysis ◽  
Low Pressure ◽  
Low Pressure Turbine ◽  
Turbine Design ◽  
Highly Loaded

Pressure Surface Separations in Low Pressure Turbines: Part 2 of 2 — Interactions With the Secondary Flow

2001 ◽  
Author(s):  
Michael J. Brear ◽  
Howard P. Hodson ◽  
Paloma Gonzalez ◽  
Neil W. Harvey
Keyword(s):  
Secondary Flow ◽  
Turbine Blades ◽  
Low Pressure ◽  
Secondary Flows ◽  
Suction Surface ◽  
Linear Cascade ◽  
Surface Separation ◽  
Pressure Surface ◽  
Low Pressure Turbine ◽  
Turbine Design

This paper describes a study of the interaction between the pressure surface separation and the secondary flow on low pressure turbine blades. It is found that this interaction can significantly affect the strength of the secondary flow and the loss that it creates. Experimental and numerical techniques are used to study the secondary flow in a family of four low pressure turbine blades in linear cascade. These blades are typical of current designs, share the same suction surface and pitch, but have differing pressure surfaces. A mechanism for the interaction between the pressure surface separation and the secondary flow is proposed and is used to explain the variations in the secondary flows of the four blades. This mechanism is based on simple dynamical secondary flow concepts and is similar to the aft-loading argument commonly used in modern turbine design.

An Experimental Flow Investigation of Low Pressure Turbine Stages With Various Wet Conditions

2012 ◽  
Author(s):  
Naoki Shibukawa ◽  
Tomohiko Tsukuda ◽  
Tadayuki Hashidate ◽  
Hiroyuki Kawagishi ◽  
Tatsuro Uchida ◽  
...  
Keyword(s):  
Steam Turbine ◽  
Flow Characteristics ◽  
Water Concentration ◽  
Low Pressure ◽  
Operating Conditions ◽  
Flow Coefficient ◽  
Low Pressure Turbine ◽  
Large Size ◽  
Flow Investigation ◽  
Turbine Design

Detail flow characteristics of an actual size low pressure steam turbine stages under real operating conditions were examined in this paper. The main purpose of the experimental work was to obtain the radial distribution of the velocity triangles in the wet flow of the large size turbine, so that a series of tests were carried out with various wet conditions. Some particular changes of the flow pattern were observed at the exit of both the stator and the blade rows which would not predicted by steam turbine design tools. A kind of flow coefficient was defined and investigated as well as the steam velocities. With an assumption of the steam wetness distribution along the blade span, a tendency of the flow coefficient was appeared which was similar to previous work [7]. The wetness assumption was qualitatively verified by bore-scope observation of the water concentration on the stator surface and the fog condition of the steam path.

Effect of the Structural Coupling on the Flutter Onset of a Sector of Low-Pressure Turbine Vanes

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Ruben Antona ◽  
Roque Corral ◽  
Juan M. Gallardo
Keyword(s):  
Three Dimensional ◽  
Low Pressure ◽  
Mode Interaction ◽  
Coupled Analysis ◽  
Three Dimensional Model ◽  
Structural Coupling ◽  
Low Pressure Turbine ◽  
Turbine Vanes ◽  
Structural Methods ◽  
Fully Coupled

The effect of the structural coupling in the aeroelastic stability of a packet of low-pressure turbine vanes is studied in detail. The dynamics of a 3D sector vane is reduced to that of a simplified mass-spring model to enhance the understanding of its dynamics and to perform sensitivity studies. It is concluded that the dynamics of the simplified model retains the basic features of the finite element three-dimensional model. A linear fully coupled analysis in the frequency domain of the 3D vane sector has been conducted. It is concluded that the small structural coupling provided by the casing and the inter-stage seal is essential to explain the experimental evidences. It is shown that the use of fully coupled aero/structural methods is necessary to retain the mode interaction that takes place in this type of configurations.

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