An Assessment of a Turbofan Engine Using Catalytic Interturbine Combustion

2009 ◽  
Author(s):  
Richard Avella´n ◽  
Tomas Gro¨nstedt
Keyword(s):  
Catalytic Combustion ◽  
Substantial Reduction ◽  
Parameter Study ◽  
Preliminary Design ◽  
Nox Formation ◽  
Technical Feasibility ◽  
Turbofan Engine ◽  
High Pressure Compressor ◽  
Aero Engines ◽  
Pressure Compressor

The potential for using catalytic combustion in aero engines is discussed. Some preliminaries relating to NOx formation and material capabilities are analyzed. Various means to integrate catalytic combustors in aero engines are described. In particular, catalytic interturbine combustion is investigated both in terms of technical feasibility and through a preliminary design exercise. A thermodynamic design point study is presented analyzing a configuration with a combustor located concentrically around the engine core receiving pressurized air through an interstage high pressure compressor bleed. A parameter study of the compressor bleed ratio is presented for the configuration. A substantial reduction in NOx emissions at the expense of an increase in mission fuel consumption is observed.

Compressor Casing Preliminary Design Based on Features

2008 ◽  
Author(s):  
Stefan Bretschneider ◽  
Frank Rothe ◽  
Martin G. Rose ◽  
Stephan Staudacher
Keyword(s):  
Design Method ◽  
Design Tool ◽  
Preliminary Design ◽  
Revolution Speed ◽  
High Pressure Compressor ◽  
Design Perspective ◽  
Structural Parts ◽  
Aero Engines ◽  
The Individual ◽  
Pressure Compressor

Structural parts, such as casings, have a significant share of the overall turbo-machinery mass of modern aero-engines. Therefore preliminary design studies must aim to include the effect of such structures. For this paper compressor casings of commercial aero-engines have been investigated in terms of their design philosophy. It is shown that compressor casings have very similar designs from the preliminary design perspective, even though they appear as very complex structures in reality. The study identified design similarities from which generalized and simplified casing structures have been derived. The casing is divided into geometrically similar basic structures. Such generalized parts are each individually characterized by features. Through simplified physical design algorithms the features are then dimensioned based on blade containment conditions, pressures and temperatures. Finally a generalized form of compressor casing design is derived from the assembly of the individual parts. The derived preliminary design method of casings is no longer dependent on a known representative casing thickness. When increasing compressor characteristics such as blade numbers, diameters or revolution speed the casing design responds directly while still maintaining a characteristic shaping philosophy. Thus a scaling method based on physics rather than only geometrical identity is achieved. The method was integrated into an existing high pressure compressor preliminary design tool. The examination of the developed methodology is carried out against existing compressor designs. Results are presented and discussed.

Preliminary Design of a High Bypass Ratio Turbofan Engine

2009 ◽  
Author(s):  
Syed Muhammad Hassan Rizvi ◽  
Kenneth W. Ramsden ◽  
Vasslios Pachidis
Keyword(s):  
Pressure Ratio ◽  
Preliminary Design ◽  
Compressor Cascade ◽  
Design Study ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
High Pressure Compressor ◽  
The Uk ◽  
Bypass Ratio ◽  
Selection Of

This paper presents a preliminary design of a high bypass ratio turbofan engine which has been developed through a Masters Degree project at Cranfield University in the UK. It is well known that the design process for a new gas turbine engine requires an understanding of the interrelated requirements of aerodynamics, thermodynamics, heat transfer, materials choice and engine control. Accordingly, the designer’s solution is inevitably the result of compromises involving a large number of mostly conflicting parameters. The preliminary design study in this paper relates to assessment of a suitable engine to satisfy the specification needs of a small airliner. The particular aircraft chosen for the design is one designed by a group of master’s degree students in the College of Aeronautics at Cranfield University. The paper includes a description of that aircraft specification for which the cruise phase is chosen as a design point for the engine. The overall objective of the design is to achieve the least (practical) specific fuel consumption so as to maximize aircraft range. The paper presents the results of the iterative design study and includes the effects of turbine entry temperature, bypass ratio, overall pressure ratio and fan pressure ratio. Subsequently, a procedure for the selection of the annulus geometry for each of the turbomachinery components and the combustor is illustrated which can deliver an acceptable gas path for the entire engine. Finally, using well established compressor cascade data, an approximate method is illustrated for the prediction of the performance characteristic of the high pressure compressor of the core engine.

Advanced Exergy Analysis of a Turbofan Engine (TFE): Splitting Exergy Destruction into Unavoidable/Avoidable and Endogenous/Exogenous

2017 ◽  
Vol 0 (0) ◽  
Author(s):  
Ozgur Balli
Keyword(s):  
High Pressure ◽  
Exergy Analysis ◽  
Low Pressure ◽  
Operating Conditions ◽  
Actual Condition ◽  
Exergy Destruction ◽  
Turbofan Engine ◽  
High Pressure Compressor ◽  
Engine Components ◽  
Pressure Compressor

AbstractA conventional and advanced exergy analysis of a turbofan engine is presented in this paper. In this framework, the main exergy parameters of the engine components are introduced while the exergy destruction rates within the engine components are split into endogenous/exogenous and avoidable/unavoidable parts. Also, the mutual interdependencies among the components of the engine and realistic improvement potentials depending on operating conditions are acquired through the analysis. As a result of the study, the exergy efficiency values of the engine are determined to be 25.7 % for actual condition, 27.55 % for unavoidable condition and 30.54 % for theoretical contion, repectively. The system has low improvement potential because the unavoidable exergy destruction rate is 90 %. The relationships between the components are relatively weak since the endogenous exergy destruction is 73 %. Finally, it may be concluded that the low pressure compressor, the high pressure compressor, the fan, the low pressure compressor, the high pressure compressor and the combustion chamber of the engine should be focused on according to the results obtained.

Automated Aerodynamic Optimization of an Aggressive S-Shaped Intermediate Compressor Duct

2018 ◽  
Author(s):  
T. Stürzebecher ◽  
G. Goinis ◽  
C. Voss ◽  
H. Sahota ◽  
P. Groth ◽  
...  
Keyword(s):  
Guide Vane ◽  
Aerodynamic Optimization ◽  
Baseline Design ◽  
Separating Flow ◽  
High Pressure Compressor ◽  
Important Research Topic ◽  
Final Design ◽  
Endwall Contouring ◽  
Aero Engines ◽  
Pressure Compressor

As bypass-ratio in modern aero engines is continuously increasing over the last decades, the radial offset between low pressure compressor (LPC) and high pressure compressor (HPC), which needs to be overcome by the connecting s-shaped intermediate compressor duct (ICD), is getting higher. Due to performance and weight saving aspects the design of shorter and therefore more aggressive ducts has become an important research topic. In this paper an already aggressive design (with respect to current aero engines) of an ICD with integrated outlet guide vane (OGV) is used as a baseline for an aerodynamic optimization. The aim is to shorten the duct even further while maintaining it separation free. The optimization is broken down into two steps. In the first optimization-step the baseline design is shortened to a feasible extent while keeping weak aerodynamic restrictions. The resulting highly aggressive duct (intermediate design), which is shortened by 19 % in axial length with respect to the baseline, shows separation tendencies of low momentum fluid in the strut/hub region. For the second step, the length of the optimized duct design is frozen. By implementing new design features in the process of the optimizer, this optimization-step aims to eliminate separation and to reduce separation tendencies caused by the aggressive shortening. In particular, these features are: a nonaxisymmetric endwall contouring and parametrization of the strut and the OGV to allow for changes in lift and turning in both blade designs. By comparison of the three designs: Baseline, intermediate (separating flow) and final design, it can be shown, that it is possible to decrease length of the already aggressive baseline design even further, when adding a nonaxisymmetric endwall contouring and changes in blade shape of the strut and OGV. Flow separation can be eliminated while losses are kept low. With a more aggressive and therefore shorter duct the engine length and weight can be reduced. This in turn leads to lighter aircrafts, less fuel consumption and lower CO2 and NOx emissions.

scholarly journals Technology Making It Into Production

2009 ◽  
Vol 131 (03) ◽  
pp. 53-53
Author(s):  
Glinter Wilfert
Keyword(s):  
European Union ◽  
High Pressure ◽  
Heat Exchanger ◽  
High Speed ◽  
Low Pressure ◽  
The European Union ◽  
Low Pressure Turbine ◽  
High Pressure Compressor ◽  
Aero Engines ◽  
Pressure Compressor

This paper discusses the concept of MTU Aero Engines’ high-speed low-pressure turbine for the geared turbofan, which is based on the European Union research program ‘Clean’. Under the program, MTU developed the high-speed low-pressure turbine, the turbine centre frame, and an integrated heat exchanger. The paper also highlights that Pratt & Whitney, launched its geared turbofan (GTF) demonstrator project and asked MTU to be a partner. MTU has secured a 15 percent stake in either GTF version, which brings its high-speed low-pressure turbine, plus the first four stages of the high-pressure compressor.

Analysis on Turbine Cooling Air Bleeding of Intercooled Recuperated Turbofan Engine

2015 ◽  
Author(s):  
Hao Gong ◽  
Zhanxue Wang ◽  
Li Zhou ◽  
Xiaobo Zhang ◽  
Jingkai Wang
Keyword(s):  
High Pressure ◽  
Combustion Chamber ◽  
High Pressure Turbine ◽  
Turbofan Engine ◽  
Turbine Cooling ◽  
High Pressure Compressor ◽  
Cooling Technology ◽  
Technology Level ◽  
Cooling Air ◽  
Pressure Compressor

In order to further improve the intercooled recuperated turbofan engine (IRT) performance, the possible high pressure turbine (HPT) cooling air bleeding schemes were analyzed. There are two HPT cooling air extraction sections, i.e. the high pressure compressor exit (forward to the recuperator cold section inlet) and the combustion chamber inlet (back from the recuperator cold section outlet). The analysis results indicate that, bleeding the HPT cooling air from the combustion chamber inlet has the potential to reduce the engine specific fuel consumption. And to determine the most suitable HPT cooling air bleeding scheme, effects of allowable turbine blade metal temperature, turbine cooling technology level, engine weight addition, different intercooler and recuperator effectiveness should be taken into account.

Review on the aerodynamics of intermediate compressor duct

2020 ◽  
Vol 14 (4) ◽  
pp. 7446-7468
Author(s):  
Manish Sharma ◽  
Beena D. Baloni
Keyword(s):  
High Pressure ◽  
Pressure Loss ◽  
Flow Analysis ◽  
Outer Wall ◽  
Optimization Techniques ◽  
Optimum Pressure ◽  
Research Areas ◽  
Static Pressure Distribution ◽  
High Pressure Compressor ◽  
Pressure Compressor

In a turbofan engine, the air is brought from the low to the high-pressure compressor through an intermediate compressor duct. Weight and design space limitations impel to its design as an S-shaped. Despite it, the intermediate duct has to guide the flow carefully to the high-pressure compressor without disturbances and flow separations hence, flow analysis within the duct has been attractive to the researchers ever since its inception. Consequently, a number of researchers and experimentalists from the aerospace industry could not keep themselves away from this research. Further demand for increasing by-pass ratio will change the shape and weight of the duct that uplift encourages them to continue research in this field. Innumerable studies related to S-shaped duct have proven that its performance depends on many factors like curvature, upstream compressor’s vortices, swirl, insertion of struts, geometrical aspects, Mach number and many more. The application of flow control devices, wall shape optimization techniques, and integrated concepts lead a better system performance and shorten the duct length.  This review paper is an endeavor to encapsulate all the above aspects and finally, it can be concluded that the intermediate duct is a key component to keep the overall weight and specific fuel consumption low. The shape and curvature of the duct significantly affect the pressure distortion. The wall static pressure distribution along the inner wall significantly higher than that of the outer wall. Duct pressure loss enhances with the aggressive design of duct, incursion of struts, thick inlet boundary layer and higher swirl at the inlet. Thus, one should focus on research areas for better aerodynamic effects of the above parameters which give duct design with optimum pressure loss and non-uniformity within the duct.

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