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.

Prospects for the creation of high-temperature heatresistant alloys based on refractory matrices and natural composites

2021 ◽  
pp. 64-78
Author(s):  
E. N. Kablov ◽  
Yu. A. Bondarenko ◽  
M. Yu. Kolodyazhny ◽  
V. A. Surova ◽  
A. R. Narsky
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
High Heat ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Heat Resistant ◽  
High Temperature Materials ◽  
Natural Composites ◽  
Scientific Technical ◽  
The Creation

The paper presents the scientific, technical and technological aspects in the field of creating new high-temperature materials for parts of the hot section of gas turbine engines (GTE) with operating temperatures exceeding those existing in GTE. More refractory metallic materials for the creation of new high-heat-resistant alloys used for the manufacture of rotor and nozzle blades and other parts of promising gas turbine engines based on NiAl-Ni3Al, Co-Cr-Re, Pt-Al, Nb-Si, Mo-Si-B systems have been investigated. It is shown that, depending on the composition of the selected matrix, the working temperature of heat-resistant alloys increases to 1300-1500°С, which is significantly higher than the existing nickel heat-resistant alloys.

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.

scholarly journals SELECTION OF TOOL HARD ALLOY FOR PROCESSING PARTS OF GAS TURBINE ENGINES

2018 ◽  
pp. 89-93
Author(s):  
E. V. Artamonov ◽  
A. M. Tveryakov ◽  
A. S. Shtin
Keyword(s):  
Hard Alloy ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Heat Resistant ◽  
Materials Used ◽  
Selection Of

The article reports a brief overview of the choice of tool hard alloy for processing heat-resistant materials used for the manufacturing of parts of gas turbine engines DR-59, J-59, and DG-90.

Calculation of temperature fields in the zone of the transverse edge of the drill

2021 ◽  
pp. 79-84
Author(s):  
Keyword(s):  
Gas Turbine ◽  
Temperature Fields ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Heat Resistant ◽  
Edge Temperature ◽  
Hole Machining

The wear of the transverse edge of the drill, the features of the drill web and the calculation determination of the temperature fields in the zone of its operation are investigated. Dependences are obtained for determining the total contact temperatures on the front and rear surfaces of the half-web. The results were used to create CAD for blade hole machining modes with application to the processing of heat-resistant materials of gas turbine engines. Keywords: hole, blade processing, drilling, transverse edge, temperature fields. [email protected]

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.

Preparation, Structure, and Properties of Ni3Al and NiAl Light Powder Alloys for Aerospace

2007 ◽  
Vol 534-536 ◽  
pp. 1585-1588 ◽  
Author(s):  
K.B. Povarova ◽  
O.A. Skachkov
Keyword(s):  
Gas Turbine ◽  
New Technology ◽  
Turbine Engines ◽  
Heat Sources ◽  
Gas Turbine Engines ◽  
Combustion Chambers ◽  
Term Operation ◽  
Heat Resistant ◽  
Turbine Installation

New light super-heat-resistant powder Ni3Al and NiAl-based alloys (of the Ni-Al-Mo-B, Ni-Al-Fe-La, and Ni-Al-Y2O3 systems), as well as a new technology for preparing and processing them have been developed. The density of the alloys was 7.3-7.5 and ~6 g/cm 3, respectively. The Ni3Al sheets were used to prepare shields for combustion chambers in gas-turbine engines by roomtemperature deformation; the shields are intended for the long-term operation at 1100-1200°C and for the short-term use at 1300°C. The activated NiAl powders alloyed with Fe+La were used to produce sintered complex-shape articles, such as combustion stabilizers in a jet unit of combustion chamber of the gas-turbine installation, heat sources, etc. capable of operating at t≤1500°C under low mechanical stresses. At 1100, 1300, and 1500°C, the 100-h strength of the heat-resistant NiAl- (2-7.5) vol. % Y2O3 alloys subjected to directional recrystallization is 70, 35 and ≥10 MPa, respectively. The vanes, in which the length of recrystallized grain is smaller than the vane length by a factor of 1.5-2, were manufactured from these alloys.

scholarly journals Integration of On-Line and Off-Line Diagnostic Algorithms for Aircraft Engine Health Management

2007 ◽  
Author(s):  
Takahisa Kobayashi ◽  
Donald L. Simon
Keyword(s):  
Gas Turbine ◽  
Health Management ◽  
Diagnostic Algorithm ◽  
Aircraft Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Simulation Environment ◽  
Diagnostic Algorithms ◽  
Engine Model ◽  
On Line

This paper investigates the integration of on-line and off-line diagnostic algorithms for aircraft gas turbine engines. The on-line diagnostic algorithm is designed for in-flight fault detection. It continuously monitors engine outputs for anomalous signatures induced by faults. The off-line diagnostic algorithm is designed to track engine health degradation over the lifetime of an engine. It estimates engine health degradation periodically over the course of the engine’s life. The estimate generated by the off-line algorithm is used to “update” the on-line algorithm. Through this integration, the on-line algorithm becomes aware of engine health degradation, and its effectiveness to detect faults can be maintained while the engine continues to degrade. The benefit of this integration is investigated in a simulation environment using a nonlinear engine model.

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