Automated Welding of Turbine Blades

1990 ◽  
Vol 112 (4) ◽  
pp. 550-554
Author(s):  
J. Liburdi ◽  
P. Lowden ◽  
C. Pilcher
Keyword(s):  
High Pressure ◽  
Turbine Blade ◽  
Heat Input ◽  
Turbine Blades ◽  
Welding Parameters ◽  
Weld Deposit ◽  
Low Pressure Turbine ◽  
High Pressure Compressor ◽  
Automation Technology ◽  
Pressure Compressor

The welding of superalloys has been regarded, generally, as an art requiring the highest degree of welder skill and discipline. These highly alloyed materials are prone to micro-cracking and, in some cases, even the best welders cannot achieve satisfactory results. Now, however, advances in automation technology have made it possible to program precisely the complex airfoil shapes and the welding parameters. Consequently, turbine blades can be welded in a repeatable manner, with a minimum of heat input, resulting in better metallurgical quality both in the base metal and the weld deposit. The application of this technology to the automated welding of high-pressure compressor turbine blade tips and the refurbishment of low-pressure turbine blade shrouds are presented in this paper.

scholarly journals Automated Welding of Turbine Blades

1989 ◽  
Author(s):  
J. Liburdi ◽  
P. Lowden ◽  
C. Pilcher
Keyword(s):  
High Pressure ◽  
Turbine Blade ◽  
Heat Input ◽  
Turbine Blades ◽  
Welding Parameters ◽  
Weld Deposit ◽  
Low Pressure Turbine ◽  
High Pressure Compressor ◽  
Automation Technology ◽  
Pressure Compressor

The welding of superalloys has been regarded, generally, as an art requiring the highest degree of welder skill and discipline. These highly alloyed materials are prone to micro-cracking and, in some cases, even the best welders cannot achieve satisfactory results. Now, however, advances in automation technology have made it possible to program precisely the complex airfoil shapes and the welding parameters. Consequently, turbine blades can be welded in a repeatable manner, with a minimum of heat input resulting in better metallurgical quality both in the base metal and the weld deposit. The application of this technology to the automated welding of high-pressure compressor turbine blade tips, and the refurbishment of low-pressure turbine blade shrouds are presented in this paper.

scholarly journals Surface Quality of Amilled Gamma Titaniumaluminide for Aeronautical Applications

2014 ◽  
Vol 5 (2) ◽  
pp. 60-65
Author(s):  
Grzegorz Radkowski ◽  
Jaroslaw Sep
Keyword(s):  
High Pressure ◽  
Titanium Aluminide ◽  
Titanium Aluminides ◽  
Turbine Blades ◽  
Low Pressure ◽  
Aviation Industry ◽  
Gamma Titanium ◽  
Low Pressure Turbine ◽  
High Pressure Compressor ◽  
Pressure Compressor

Abstract Gamma titanium aluminides are an interesting alternative for nickel, iron or cobalt matrix superalloys. Due to the advantageous strength properties at high temperatures they can successfully replace superalloys in applications such as high pressure compressor blades, low pressure turbine blades, high pressure compressor case, low pressure turbine case. Milling is one of the processes that can be applied in the forming elements made from this type of alloys for the aviation industry. Research included the selection of tool, the process kinematics and the range of milling gamma titanium aluminide (Ti-45Al-5Nb-0.2B-0.2C) process parameters were carried out. Milling can be an effective method of forming of elements made of gamma TiAL in the range of processing parameters: vc = 20-70 m/min, ap = 0.3-0.7 mm, fz = 0.1- 0.45 mm/tooth. In the tests carried out the best results were obtained using a R300-016A20L- 08L milling cutter, S30T tool coating and in-cut milling.

Forging of Titaniumaluminide Parts

2010 ◽  
Vol 638-642 ◽  
pp. 1353-1356 ◽  
Author(s):  
Peter Janschek
Keyword(s):  
Turbine Blades ◽  
High Heat ◽  
Strain Rates ◽  
Lightweight Construction ◽  
Compressor Blades ◽  
Low Pressure Turbine ◽  
High Temperature Mechanical Properties ◽  
High Pressure Compressor ◽  
New Material ◽  
Pressure Compressor

A new material is available that displays the high temperature mechanical properties of nickel alloys at half the density –the intermetallic Titaniumaluminides. These extraordinary properties give it great potential for lightweight construction in aeroengines. The high Young’s modulus compared to common Titanium alloys offers advantages even in light weight applications, which do not need high heat resistance, e. g. connection rods. However, its characteristic rather like ceramics than metals presents a challenge in terms of forming. A forging technology has been developed with respect to this behaviour. Using isothermal forging at high temperatures with extremely low strain rates allows a material related forming. High pressure compressor blades and low pressure turbine blades have been forged as well as con rod for sports car engines. For economical improvement several blades may be forged at the same time.

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.

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.

scholarly journals Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions

2014 ◽  
Author(s):  
Alain Batailly ◽  
Mathias Legrand ◽  
Antoine Millecamps ◽  
Sèbastien Cochon ◽  
François Garcin
Keyword(s):  
High Pressure ◽  
Forced Response ◽  
Compressor Blade ◽  
Design Stage ◽  
Blade Design ◽  
Early Integration ◽  
Nonlinear Structural ◽  
High Pressure Compressor ◽  
Structural Interactions ◽  
Pressure Compressor

Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-pressure compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.

A Machine Learning Based Approach of Performance Estimation for High-Pressure Compressor Airfoils

2018 ◽  
Author(s):  
Jonas Marx ◽  
Stefan Gantner ◽  
Jörn Städing ◽  
Jens Friedrichs
Keyword(s):  
Machine Learning ◽  
High Pressure ◽  
Machine Learning Algorithms ◽  
Performance Estimation ◽  
Predictive Maintenance ◽  
Support Vector ◽  
K Nearest Neighbor ◽  
Operating Characteristics ◽  
High Pressure Compressor ◽  
Pressure Compressor

In recent years, the demands of Maintenance, Repair and Overhaul (MRO) customers to provide resource-efficient after market services have grown increasingly. One way to meet these requirements is by making use of predictive maintenance methods. These are ideas that involve the derivation of workscoping guidance by assessing and processing previously unused or undocumented service data. In this context a novel approach on predictive maintenance is presented in form of a performance-based classification method for high pressure compressor (HPC) airfoils. The procedure features machine learning algorithms that establish a relation between the airfoil geometry and the associated aerodynamic behavior and is hereby able to divide individual operating characteristics into a finite number of distinct aero-classes. By this means the introduced method not only provides a fast and simple way to assess piece part performance through geometrical data, but also facilitates the consideration of stage matching (axial as well as circumferential) in a simplified manner. It thus serves as prerequisite for an improved customary HPC performance workscope as well as for an automated optimization process for compressor buildup with used or repaired material that would be applicable in an MRO environment. The methods of machine learning that are used in the present work enable the formation of distinct groups of similar aero-performance by unsupervised (step 1) and supervised learning (step 2). The application of the overall classification procedure is shown exemplary on an artificially generated dataset based on real characteristics of a front and a rear rotor of a 10-stage axial compressor that contains both geometry as well as aerodynamic information. In step 1 of the investigation only the aerodynamic quantities in terms of multivariate functional data are used in order to benchmark different clustering algorithms and generate a foundation for a geometry-based aero-classification. Corresponding classifiers are created in step 2 by means of both, the k Nearest Neighbor and the linear Support Vector Machine algorithms. The methods’ fidelities are brought to the test with the attempt to recover the aero-based similarity classes solely by using normalized and reduced geometry data. This results in high classification probabilities of up to 96 % which is proven by using stratified k-fold cross-validation.

Elimination of unstable free vibrations of the rotor of a centrifugal high-pressure compressor

1988 ◽  
Vol 24 (7) ◽  
pp. 356-360
Author(s):  
V. B. Shnepp ◽  
A. M. Galeev ◽  
G. S. Batkis ◽  
V. M. Polyakov
Keyword(s):  
High Pressure ◽  
Free Vibrations ◽  
High Pressure Compressor ◽  
Pressure Compressor
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