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.

Redesign of High-Lift LP-Turbine Airfoils for Low Speed Testing

2010 ◽  
Author(s):  
Michele Marconcini ◽  
Filippo Rubechini ◽  
Roberto Pacciani ◽  
Andrea Arnone ◽  
Francesco Bertini
Keyword(s):  
Separated Flow ◽  
Low Pressure ◽  
High Lift ◽  
Low Speed ◽  
Low Pressure Turbine ◽  
Wide Range ◽  
Flow Configurations ◽  
Artificial Neural Network Ann ◽  
Lp Turbine ◽  
Turbine Airfoils

Low pressure turbine airfoils of the present generation usually operate at subsonic conditions, with exit Mach numbers of about 0.6. To reduce the costs of experimental programs it can be convenient to carry out measurements in low speed tunnels in order to determine the cascades performance. Generally speaking, low speed tests are usually carried out on airfoils with modified shape, in order to compensate for the effects of compressibility. A scaling procedure for high-lift, low pressure turbine airfoils to be studied in low speed conditions is presented and discussed. The proposed procedure is based on the matching of a prescribed blade load distribution between the low speed airfoil and the actual one. Such a requirement is fulfilled via an Artificial Neural Network (ANN) methodology and a detailed parameterization of the airfoil. A RANS solver is used to guide the redesign process. The comparison between high and low speed profiles is carried out, over a wide range of Reynolds numbers, by using a novel three-equation, transition-sensitive, turbulence model. Such a model is based on the coupling of an additional transport equation for the so-called laminar kinetic energy (LKE) with the Wilcox k–ω model and it has proven to be effective for transitional, separated-flow configurations of high-lift cascade flows.

Study of Flow Controlling on LP Turbine at Different Reynolds Number

2012 ◽  
Author(s):  
Muhammad Aqib Chishty ◽  
Hossein Raza Hamdani ◽  
Khalid Parvez ◽  
Muhammad Nafees Mumtaz Qadri
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Flow Separation ◽  
Separation Bubble ◽  
Low Pressure ◽  
Control Flow ◽  
Loss Coefficient ◽  
Shear Stresses ◽  
Low Pressure Turbine ◽  
Lp Turbine

Active and passive techniques have been used in the past, to control flow separation. Numerous studies were published on controlling and delaying the flow separation on low pressure turbine. In this study, a single dimple (i.e. passive device) is engraved on the suction side of LP turbine cascade T106A. The main aim of this research is to find out the optimum parameters of dimple i.e. diameter (D) and depth (h) which can produce strong enough vortex that can control the flow either in transition or fully turbulent phase. Furthermore, this optimal dimple is engraved to suppress the boundary layer separation at different Reynolds number (based on the chord length and inlet velocity). The dimple of different depth and diameter are used to find the optimal depth to diameter ratio. Computational results show that the optimal ratio of depth to diameter (h/D) for dimple is 0.0845 and depth to grid boundary layer (h/δ) is 0.5152. This optimized dimple efficiently reduces the normalized loss coefficient and it is found that the negative values of shear stresses found in uncontrolled case are being removed by the dimple. After that, dimple of optimized parameters are used to suppress the laminar separation bubble at different Re∼25000, 50000 and 91000. It was noticed that the dimple did not reduce the losses at Re∼25000. But at Re∼50000, it produced such a strong vortex that reduced the normalized loss coefficient to 25%, while 5% losses were reduced at Re∼91000. It can be concluded that the optimized dimple effectively controlled flow separation and reduced normalized loss coefficient from Re 25000 to 91000. As the losses are decreased, this will increase the low pressure turbine efficiency and reduce its fuel consumption.

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.

The Effects of Steady Injection on an Ultra High Lift Vane in a LP Turbine

2008 ◽  
Author(s):  
Thomas Schumann ◽  
Martin G. Rose ◽  
Stephan Staudacher ◽  
Jochen Gier ◽  
Th. Schro¨der
Keyword(s):  
Steady Flow ◽  
Flow Injection ◽  
Lift Coefficient ◽  
Suction Side ◽  
Low Pressure ◽  
Control Flow ◽  
Flow Area ◽  
High Lift ◽  
Low Pressure Turbine ◽  
Lp Turbine

The application of steady flow injection to control flow separation on the suction side of an ultra high lift low pressure turbine airfoil is presented. The blade lift coefficient of the ultra high lift airfoil at 1.46 Zweifel coefficient is considerably higher than those of conventional airfoils. Blade Reynolds numbers and blade dimensions are comparable to the first stages of aero engine low pressure turbines. The ultra high lift vane row is installed into a three stage low Mach number turbine test rig. Steady flow injection through suction side streamwise holes is investigated: with an angle to the surface of 45 deg. The pitch to diameter ratio is 10. The variation of the blowing ratio allows a closer study of the influence and effects occuing due to flow injection. Results show that steady flow injection can almost completely eliminate separation on the suction side. For four different blowing ratios blade pressure distribution and exit flow area traverse shows rising stage loading. A maximum of one percent change in flow exit angle was measured. The experimental results reveal that the injection jets only locally suppress the separation. This results in a spanwise variation in lift and trailing edge shed vortical structures.

Aerodynamic Design of High End Wall Angle Turbine Stages—Part I: Methodology Development

2013 ◽  
Vol 136 (2) ◽  
Author(s):  
A. W. Cranstone ◽  
G. Pullan ◽  
E. M. Curtis ◽  
S. Bather
Keyword(s):  
Surface Pressure ◽  
Design Methodology ◽  
Low Pressure ◽  
Similar Magnitude ◽  
Aerodynamic Design ◽  
Wall Angle ◽  
Methodology Development ◽  
Low Pressure Turbine ◽  
Turbine Vanes ◽  
End Wall

A design methodology is presented for turbines in an annulus with high end wall angles. Such stages occur where large radial offsets between the stage inlet and stage outlet are required, for example in the first stage of modern low pressure turbines, and are becoming more prevalent as bypass ratios increase. The turbine vanes operate within s-shaped ducts which result in meridional curvature being of a similar magnitude to the blade-to-blade curvature. Through a systematic series of idealized computational cases, the importance of two aspects of vane design are shown. First, the region of peak end wall meridional curvature is best located within the vane row. Second, the vane should be leant so as to minimize spanwise variations in surface pressure—this condition is termed “ideal lean.” This design philosophy is applied to the first stage of a low pressure turbine with high end wall angles.

scholarly journals The Influence of a Variable Capacity Turbine in the Performance of a Variable Cycle Engine

1999 ◽  
Author(s):  
Martin Dodds ◽  
Pericles Pilidis
Keyword(s):  
Low Pressure ◽  
Variable Geometry ◽  
Variable Flow ◽  
Low Pressure Turbine ◽  
Extensive Variable ◽  
Variable Capacity ◽  
Lp Turbine ◽  
The Cost ◽  
Engine Components ◽  
Bypass Ratio

An investigation was conducted to examine the effects of a variable flow low pressure turbine on a variable cycle engine’s performance. One of the greatest challenges, during the design of a variable cycle engine is how to optimise the various cycles and then to match then to the capabilities of the engine components, the use of extensive variable geometry is required to achieve this. A method of matching variable cycle engines that was developed Cranfield University was adapted to cater for the use of a variable flow low pressure turbine. It was discovered that the implementation of variable geometry within the low pressure turbine could significantly reduce the requirements for variable geometry within the compressor system, at the cost of replacing well proven compressor variable geometry with high risk technology within the LP turbine. Utilising the variable flow turbine to expand the bypass ratio range of the engine was studied. Increasing the LPM bypass ratio to 1.1 and 1.2 yielded SFC reductions of 3% and 5% respectively, reducing the bypass ratio of the HPM to 0.1 gave a 20% increase in specific thrust. It was found that the performance benefits gained from expanding the bypass ratio are large enough to warrant further investigation into this concept.

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
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