Development of Innovative Coating Technology, MSCoating, Using Electrical Discharge

2010 ◽  
Author(s):  
Yoshikazu Nakano ◽  
Takeshi Araki ◽  
Akira Yamada ◽  
Hiroyuki Teramoto ◽  
Masahiro Okane ◽  
...  
Keyword(s):  
High Reliability ◽  
Pulse Discharge ◽  
Turbine Blades ◽  
Wear Test ◽  
Low Pressure ◽  
Fretting Wear ◽  
Wear Performance ◽  
Coating Technology ◽  
Low Pressure Turbine ◽  
Wear Coating

MSCoating is a new coating technology using pulse discharge. This coating technology, which is developed by Mitsubishi Electric and IHI, has been put into practical use as an anti-wear coating for low-pressure turbine blades in aero engines. Normally, Z-notch, which is the edge of a low-pressure turbine blade in an aero engine, is treated with anti-wear coating by welding because these edges are frictioned together while the engine is running. However, coating by welding requires pre-heating, removal of excess thickness and advanced skill to ensure high reliability. Therefore, improvement of productivity and cost reduction are required for the anti-wear coating of Z-notch. MSCoating is an innovative coating technology that is able to meet these requirements. MSCoating can eliminate the above processing needed for coating by welding, and has superb productivity and reliability for machine work. It is confirmed that anti-wear performance of the coating formed by MSCoating is about 10 times as high as that formed by welding in a fretting wear test under conditions similar to the real operating condition. It is suggested that hard precipitate such as carbide and oxide of chrome and cobalt oxide in the MSCoating layer play a role in the advantages of the anti-wear performance.

Cracks on the Roots of Turbine Blades of the Low-Pressure Turbine in a Steam Power Plant

2015 ◽  
Vol 52 (4) ◽  
pp. 214-225 ◽  
Author(s):  
E. Plesiutschnig ◽  
R. Vallant ◽  
G. Stöfan ◽  
C. Sommitsch ◽  
M. Mayr ◽  
...  
Keyword(s):  
Power Plant ◽  
Turbine Blades ◽  
Low Pressure ◽  
Steam Power ◽  
Steam Power Plant ◽  
Low Pressure Turbine

Analysis on High Rates of Scaling and Salt Accumulation of 600MW Supercritical once-through Boiler

2012 ◽  
Vol 166-169 ◽  
pp. 620-626
Author(s):  
Xiao Ni Zhang ◽  
Xian Min Li ◽  
Chang Ming Li
Keyword(s):  
Turbine Blades ◽  
Low Pressure ◽  
Fossil Plants ◽  
Salt Accumulation ◽  
Accelerated Corrosion ◽  
Low Pressure Turbine ◽  
Salt Deposition ◽  
Boiler Units ◽  
Salt Deposits ◽  
Flow Accelerated Corrosion

The chemistry check-ups were reviewed in the first maintenance of 600 MW supercritical once-through boiler units in Henan. Several problems were found: (1) high rates of scaling on the waterwall and economizer; (2) high rates of salt deposition on the turbine blades; (3) the formation of salt deposits on blades were complicated; (4) corrosion of low pressure turbine blades in period of maintenance was a universal phenomenon; (5) FAC (flow-accelerated corrosion) were most frequent in HP heaters and HP drain lines in most fossil plants. The reasons have been analyzed and the suggestions have been provided.

The Science, Technology, and Implementation of TiAl Alloys in Commercial Aircraft Engines

2013 ◽  
Vol 1516 ◽  
pp. 49-58 ◽  
Author(s):  
B. P. Bewlay ◽  
M. Weimer ◽  
T. Kelly ◽  
A. Suzuki ◽  
P.R. Subramanian
Keyword(s):  
Titanium Aluminide ◽  
Turbine Blades ◽  
Aircraft Engine ◽  
Low Pressure ◽  
Major Advance ◽  
Commercial Aircraft ◽  
Tial Alloys ◽  
Low Pressure Turbine ◽  
Titanium Aluminide Alloy ◽  
History Of

ABSTRACTThe present article will describe the science and technology of titanium aluminide (TiAl) alloys and the engineering development of TiAl for commercial aircraft engine applications. The GEnxTM engine is the first commercial aircraft engine that is flying titanium aluminide (alloy 4822) blades and it represents a major advance in propulsion efficiency, realizing a 20% reduction in fuel consumption, a 50% reduction in noise, and an 80% reduction in NOx emissions compared with prior engines in its class. The GEnxTM uses the latest materials and design processes to reduce weight, improve performance, and reduce maintenance costs.GE’s TiAl low-pressure turbine blade production status will be discussed along with the history of implementation. In 2006, GE began to explore near net shape casting as an alternative to the initial overstock conventional gravity casting plus machining approach. To date, more than 40,000 TiAl low-pressure turbine blades have been manufactured for the GEnxTM 1B (Boeing 787) and the GEnxTM 2B (Boeing 747-8) applications. The implementation of TiAl in other GE and non-GE engines will also be discussed.

scholarly journals Flutter Mechanisms in Low Pressure Turbine Blades

1998 ◽  
Author(s):  
M. Nowinski ◽  
J. Panovsky
Keyword(s):  
Research Effort ◽  
Turbine Blades ◽  
Low Pressure ◽  
Design Parameters ◽  
Computational Techniques ◽  
Influence Coefficient ◽  
Low Pressure Turbine ◽  
Blade Flutter ◽  
Euler Methods ◽  
Annular Cascade

The work described in this paper is part of a comprehensive research effort aimed at eliminating the occurrence of low pressure turbine blade flutter in aircraft engines. The results of fundamental unsteady aerodynamic experiments conducted in an annular cascade are studied in order to improve the overall understanding of the flutter mechanism and to identify the key flutter parameters. In addition to the standard traveling wave tests, several other unique experiments are described. The influence coefficient technique is experimentally verified for this class of blades. The beneficial stabilizing effect of mistuning is also directly demonstrated. Finally, the key design parameters for flutter in low pressure turbine blades are identified. In addition to the experimental effort, correlating analyses utilizing linearized Euler methods demonstrate that these computational techniques are adequate to predict turbine flutter.

Flutter of Low Pressure Turbine Blades With Cyclic Symmetric Modes: A Preliminary Design Method

2004 ◽  
Vol 126 (2) ◽  
pp. 306-309 ◽  
Author(s):  
Robert Kielb ◽  
Jack Barter ◽  
Olga Chernycheva ◽  
Torsten Fransson
Keyword(s):  
Mode Shape ◽  
Design Method ◽  
Turbine Blades ◽  
Current Method ◽  
Low Pressure ◽  
Mode Shapes ◽  
Preliminary Design ◽  
Complex Mode ◽  
Low Pressure Turbine ◽  
Reduced Frequency

A current preliminary design method for flutter of low pressure turbine blades and vanes only requires knowledge of the reduced frequency and mode shape (real). However, many low pressure turbine (LPT) blade designs include a tip shroud that mechanically connects the blades together in a structure exhibiting cyclic symmetry. A proper vibration analysis produces a frequency and complex mode shape that represents two real modes phase shifted by 90 deg. This paper describes an extension to the current design method to consider these complex mode shapes. As in the current method, baseline unsteady aerodynamic analyses must be performed for the three fundamental motions, two translations and a rotation. Unlike the current method work matrices must be saved for a range of reduced frequencies and interblade phase angles. These work matrices are used to generate the total work for the complex mode shape. Since it still only requires knowledge of the reduced frequency and mode shape (complex), this new method is still very quick and easy to use. Theory and an example application are presented.

scholarly journals Application of Laser Peening Technology for Low-Pressure Turbine Blades

2020 ◽  
Vol 42 (6) ◽  
pp. 467
Author(s):  
Itaru CHIDA ◽  
Yuji SANO ◽  
Keiichi HIROTA ◽  
Takao INUKAI ◽  
Rie SUMIYA ◽  
...  
Keyword(s):  
Turbine Blades ◽  
Low Pressure ◽  
Laser Peening ◽  
Low Pressure Turbine

Effect of Sector Mode Shape Variation on the Aerodynamic Stability of a Low-Pressure Turbine Sectored Vane

2003 ◽  
Author(s):  
Olga V. Chernysheva ◽  
Torsten H. Fransson ◽  
Robert E. Kielb ◽  
John Barter
Keyword(s):  
Turbine Blades ◽  
Low Pressure ◽  
Mode Shapes ◽  
Two Dimensional ◽  
Shape Variation ◽  
Aerodynamic Stability ◽  
Flow Solver ◽  
Low Pressure Turbine ◽  
Influence Coefficients

The paper presents a method to investigate the flutter appearance in a cascade, where blades are connected together in a number of identical sectors. The key parameters of the method are vibration amplitudes and mode shapes of the blades belonging to the same sector. The aerodynamic response from a sectored vane cascade is calculated based on the aerodynamic work influence coefficients of freestanding blades performed with two-dimensional inviscid linearized flow solver. A case study based upon the presented methodology shows that, despite stabilizing effect of tying blades together into sectors, a sectored vane consisting of six low-pressure turbine blades vibrating with real single modes, and identical amplitudes can be unstable at realistic design conditions.

Influence of Tip Shroud Modeling on the Flutter Stability of a Low Pressure Turbine Rotor

2019 ◽  
Author(s):  
Lorenzo Pinelli ◽  
Federico Vanti ◽  
Andrea Arnone ◽  
Benjamin Beßling ◽  
Damian M. Vogt
Keyword(s):  
Modal Analysis ◽  
Open Source ◽  
Linear Method ◽  
Turbine Blades ◽  
Low Pressure ◽  
Turbine Rotor ◽  
Contact Interface ◽  
Aerodynamic Damping ◽  
Low Pressure Turbine ◽  
Tip Shroud

Abstract Since the modern design trend of low pressure turbine blades for aeronautical propulsion leads to lighter and more loaded blades, thus prone to flutter induced vibrations; flutter assessment is now a standard verification within the design loop of these components. Flutter stability assessment requires FEM and CFD tools able to predict the pressure response of fluid flow due to blade oscillation in order to compute the aerodynamic damping. Such tools are mature and validated, yet some geometrical aspects of the blade-row as contact interfaces at the blade tip shroud have to be carefully simulated to obtain accurate flutter results. The aim of this paper is to demonstrate the capability of the Open Source FEM tool (CalculiX) to deal with complex interlocked rotor geometries when performing modal analysis and to show the influence of different contact interface modeling on flutter stability. The solid mesh of a single-pitch row sector has been generated by using the Open Source suite Salome and the modal analysis has been carried out with CalculiX with cyclic symmetry conditions. The following uncoupled flutter simulations have been performed with the CFD TRAF code, an in-house solver developed at the University of Florence, which implements a non-linear method for flutter evaluation. An in-depth comparison among the FEM models with different boundary conditions in terms of mode shape frequency and aerodynamic damping curves are reported. These results show the effect of different contact interface models, especially on the first bending mode family, and confirm the overall row stability detected during a dedicated experimental flutter campaign.

ICONE19-43291 Development of laser peening technology for low pressure turbine blades

2011 ◽  
Vol 2011.19 (0) ◽  
pp. _ICONE1943-_ICONE1943
Author(s):  
Itaru Chida ◽  
Keiichi Hirota ◽  
Yuji Sano ◽  
Hidekazu Sasaki ◽  
Rie Sumiya ◽  
...  
Keyword(s):  
Turbine Blades ◽  
Low Pressure ◽  
Laser Peening ◽  
Low Pressure Turbine
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