scholarly journals TECHNOLOGY FOR RESTORATION AND REPAIR OF AIRCRAFT ENGINE PARTS

Aviation ◽  
2021 ◽  
Vol 25 (4) ◽  
pp. 262-267
Author(s):  
Serhii Nyzhnyk ◽  
Ihor Zorik ◽  
Kostiantyn Danko ◽  
Justas Nugaras
Keyword(s):  
Titanium Alloy ◽  
Substrate Surface ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Technological Parameters ◽  
Detonation Spraying ◽  
Compressor Blades ◽  
Complex Technology ◽  
Spraying Process

Problems of increasing the service life of compressor blades of aircraft gas turbine engines using detonation spraying technology are considered. The simulation of the parameters of the velocity and temperature of the particles of the sprayed material in the barrel of the detonation unit and in the flooded space to the substrate was carried out, followed by the choice of the optimal technological parameters of the spraying process. The control system of the detonation unit has been modernized. An experiment was carried out on the deposition of the Al2O3 coatings on the samples of a substrate made of titanium alloy VT3-1. Based on the results of the experiment, technological recommendations were developed concerning both the parameters of the spraying process and the parameters of the preparation of the substrate surface before spraying. The equipment for brazing the blades of the guide vanes is described and a device for spraying coatings on the end surfaces of the compressor blades is proposed. Thus, a complex technology has been developed for restoring the end surfaces of titanium alloy compressor blades by deposition of Al2O3 coatings.

Practical Implications of Integrating Turbomachinery Into the Air Turborocket

2004 ◽  
Author(s):  
Joshua A. Clough ◽  
Mark J. Lewis
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Launch Vehicle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Space Launch ◽  
Practical Implications

The development of new reusable space launch vehicle concepts has lead to the need for more advanced engine cycles. Many two-stage vehicle concepts rely on advanced gas turbine engines that can propel the first stage of the launch vehicle from a runway up to Mach 5 or faster. One prospective engine for these vehicles is the Air Turborocket (ATR). The ATR is an innovative aircraft engine flowpath that is intended to extend the operating range of a conventional gas turbine engine. This is done by moving the turbine out of the core engine flow, alleviating the traditional limit on the turbine inlet temperature. This paper presents the analysis of an ATR engine for a reusable space launch vehicle and some of the practical problems that will be encountered in the development of this engine.

scholarly journals Advanced Technology for Reducing Aircraft Engine Pollution

1974 ◽  
Vol 96 (4) ◽  
pp. 1354-1360 ◽  
Author(s):  
R. E. Jones
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Advanced Technology ◽  
Turbine Engines ◽  
Variable Geometry ◽  
Gas Turbine Engines ◽  
Large Reduction ◽  
Final Phase ◽  
Fuel Staging ◽  
Develop Technology

The proposed EPA regulations covering emissions of gas turbine engines will require extensive combustor development. The NASA is working to develop technology to meet these goals through a wide variety of combustor research programs conducted in-house, by contract, and by university grant. In-house efforts using the swirl-can modular combustor have demonstrated sizable reduction in NOx emission levels. Testing to reduce idle pollutants has included the modification of duplex fuel nozzles to air-assisted nozzles and an exploration of the potential improvements possible with combustors using fuel staging and variable geometry. The Experimental Clean Combustor Program, a large contracted effort, is devoted to the testing and development of combustor concepts designed to achieve a large reduction in the levels of all emissions. This effort is planned to be conducted in three phases with the final phase to be an engine demonstration of the best reduced emission concepts.

REMOVAL OF HARDENING COATINGS BASED ON TITANIUM NITRIDE AND ZIRCONIUM NITRIDE FROM THE SURFACE OF PARTS MADE OF TITANIUM ALLOYS

2020 ◽  
pp. 113-121
Author(s):  
D.A. Dobrynin ◽  
◽  
I.V. Iatsyuk ◽  
O.N. Doronin ◽  
◽  
...  
Keyword(s):  
Titanium Nitride ◽  
Titanium Alloys ◽  
Gas Turbine ◽  
Zirconium Nitride ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Compressor Blades ◽  
Hardening Coatings ◽  
Electrochemical Removal

Рrovides an overview of the methods of chemical and electrochemical removal of hardening coatings based on titanium nitride (TiN) and zirconium nitride (ZrN) from the surface of parts made of various materials that can be used to remove defective and waste coatings from the surface of compressor blades and other parts of gas turbine engines (GTE) from titanium alloys. The main disadvantages of the described methods are shown in relation to the removal of hardening coatings from the surface of compressor blades and other GTE parts made of titanium alloys. Taking into account the shortcomings of the available methods, FSUE «VIAM» has developed effective methods for chemical removal of hardening coatings based on titanium nitride and zirconium nitride from the surface of parts made of titanium alloys, and recommendations are given for controlling the completeness of removal of coatings.

scholarly journals Surface layer quality in compressor titanium blades at multiaxes deep grinding

2017 ◽  
Vol 2 (12) ◽  
pp. 15-19
Author(s):  
В. Полетаев ◽  
V. Poletaev ◽  
Е. Цветков ◽  
E. Tsvetko
Keyword(s):  
Titanium Alloy ◽  
Surface Layer ◽  
Residual Stresses ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Blade Surface ◽  
A Value ◽  
Surface Layer Quality

The investigation results of technological conditions impact at multiaxes deep grinding upon quality of titanium alloy blade surface layer in the compressors of gas turbine engines (GTE) are presented. The grinding mode impact upon a surface and a value of residual stresses in a surface layer of blades is defined and also conditions for defect occurrence as burns on blade surfaces under machining are detected.

The Testing and Approval of Aircraft Engine Mounted Accessories

1982 ◽  
Vol 196 (1) ◽  
pp. 57-64
Author(s):  
D S Pearson
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Single Frequency ◽  
Turbine Engines ◽  
Severity Assessment ◽  
Gas Turbine Engines ◽  
Shaft Speed ◽  
Unified Approach ◽  
Frequency Excitation ◽  
Environmental Simulation

Vibration measurements on gas turbine engines are normally made using accelerometers. The environment to which engine accessories would be subject has been evaluated by comparing ‘g’ peaks in the frequency spectrum, individually, with empirical yardsticks of severity. Endurance approval testing of accessories to withstand the environment so characterized is normally conducted by applying unidirectional single frequency excitation to simulate engine conditions at a particular shaft speed. These procedures have proved inadequate in predicting failure or verifying corrective measures where accessory problems due to wear phenomena are concerned. This paper analyses reasons for this inadequacy in terms of measurement practice, engine severity assessment, environmental simulation and approval procedures. By recognizing the effect of multi-frequency vibration in three planes it further aims to provide a unified approach to accessory design and development by which service accessory reliability might be improved. Although at first sight more expensive, the approach described will in many cases reduce to previous practice. In cases where greater test expenditure is necessary, loopholes will have been plugged by which many expensive service problems previously escaped.

Techniques and Methods to Improve the Dynamic Strength of Gas Turbine Engines Compressor Rotor Wheels

2014 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Calculation Method ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Cfd Model ◽  
Compressor Blades ◽  
Compressor Rotor ◽  
Pressure Compressor

The approaches to reducing the alternating stresses in the compressor blades, arising at a resonance, are discussed in paper. Maximum alternating stresses in blades of the fifth stage of intermediate pressure compressor (IPC, that operating under the gas flow circumferential variation conditions, are defined on the basis of the forced blade oscillations calculation method. Parametric CFD-model which allows to introduce different stagger angles and circumferentially alternating blade pitch at the guide vanes of IPC fifth stage was created to reduce the stresses. The flow circumferential variation was reduced by changing these parameters and as a consequence the resonant stresses were decreased by more than 2.5 times.

scholarly journals Cobalt–Niobium-Carbide Eutectic Alloys for Increasing the Service Life of Gas Turbine Engines

2021 ◽  
Vol 22 (4) ◽  
pp. 678-693
Author(s):  
G. P. Dmitrieva ◽  
T. S. Cherepova ◽  
T. V. Pryadko
Keyword(s):  
Service Life ◽  
Gas Turbine ◽  
Niobium Carbide ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Eutectic Alloys ◽  
Heat Resistant ◽  
The Creation

This article represents the stages of the creation of new serial wear-proof and heat-resistant (at temperatures up to 1100 °C) cobalt–Nb-carbide cast eutectic alloys of the KhTN (XTN) grade at the G.V. Kurdyumov Institute for Metal Physics of the N.A.S. of Ukraine, comparing them by their main properties, and use in aircraft engine engineering.

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