Determination of technological heredity when machining holes in parts of gas turbine engines

2021 ◽  
pp. 37-42
Author(s):  
Keyword(s):  
Cutting Force ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Calculation Of Parameters ◽  
Technological Heredity ◽  
Hole Axis

Calculation of parameters that determine technological heredity during drilling and the ability to control the process of technological heredity. Keywords: drilling, cutting force, drift, hole axis, depth and degree of hardening, technological heredity. [email protected]

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

1990 ◽  
Author(s):  
Yoshiharu Tsujikawa ◽  
Makoto Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

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]

scholarly journals CALCULATION OF EFFECTIVE COMBUSTION PRODUCTS TEMPERATURE BEFORE THE GAS-TURBINE ENGINES POWER TURBINES

2016 ◽  
pp. 100-106
Author(s):  
S. I. Perevoschikov
Keyword(s):  
Gas Turbine ◽  
Combustion Products ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Effective Output

The article describes derivation of relationships permitting to calculate the temperature of combustion products before the power turbines of gas-turbine engines taking into account a partial return of the lost earlier power of the combustion products in the previous turbines. Using these relationships data significantly improves determination of the gas-turbine engines effective output by their operation data.

Interim Particulate Matter Test Method for the Determination of Particulate Matter from Gas Turbine Engines

2011 ◽  
Author(s):  
Robert P. Howard ◽  
Kathryn M. Stephens ◽  
Philip D. Whitefield ◽  
Donald E. Hagen ◽  
Steven L. Achterberg ◽  
...  
Keyword(s):  
Particulate Matter ◽  
Gas Turbine ◽  
Test Method ◽  
Turbine Engines ◽  
Gas Turbine Engines

scholarly journals TO DETERMINATION OF THE QUANTITY OF DANGEROUS GASES IN A GAS TURBINE HEAT-VENTILATION TUNNEL INSTALLATION

2019 ◽  
Vol 2 (4) ◽  
pp. 45-52
Author(s):  
Lavrenty Kiyanitsa ◽  
Olga Kulikova
Keyword(s):  
Nitrogen Oxides ◽  
Gas Turbine ◽  
Far East ◽  
Carbon Oxide ◽  
Hazardous Substances ◽  
Turbine Engines ◽  
Hazardous Substance ◽  
Gas Turbine Engines ◽  
Working Parameters

There is the emission problem of hazardous substances such as nitrogen oxides, carbon oxide and soot into inner space of tunnel with heated air while using of gas-turbine engines as heat ventilating equipment for long railway tunnels in conditions of harsh continental climate of Siberian and Far East. In the investigation working parameters of gas-turbine equipment based on jet engine D-36 is determined. The analysis of hazardous substance emissions for two specific working modes is carried out. It is educed that the concentration of nitrogen oxides located at ventilating flow from the equipment, working at nominal mode, do not exceed standards of maximal permissible concentrations for railway tunnels. Parameters of the surrounding air, discharged into the tunnel, for dilution of ventilating flow with high content of nitrogen oxides to standard of MPC is determined.

scholarly journals The Determination of Rational Parameters of Lock Joints of Ceramic Blades with a Metal Disk in Advanced Aircraft Gas Turbine Engines. Part I. Models of Mechanical and Thermal Contact of Ceramic and Metal Parts of the Turbine Impeller

2019 ◽  
pp. 71-81 ◽  
Author(s):  
S.V. Reznik ◽  
D.V. Sapronov ◽  
T.D. Karimbaev ◽  
M.A. Mezencev
Keyword(s):  
Tensile Strength ◽  
Gas Turbine ◽  
Thermal Contact ◽  
Metal Alloys ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Metal Parts ◽  
Metal Disk ◽  
Turbine Impeller

To increase the efficiency of aircraft gas turbine engines, it is necessary to increase the temperature of the gas before the turbine. However, metal alloys used in modern designs may not be used for this without a reduction in the durability of parts. One way to solve this problem is to develop turbine designs with ceramic elements. The issues of ensuring thermal resistance of the lock joints of turbine impellers with blades made of monolithic ceramic material are considered in this work. Models of mechanical and thermal contact of ceramic and metal parts are presented. The influence of the scale factor and stress concentration factor on the tensile strength of the ceramic parts is studied.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by an Optimization Procedure

1991 ◽  
Vol 113 (1) ◽  
pp. 100-105 ◽  
Author(s):  
Y. Tsujikawa ◽  
M. Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Method Comparison ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including the scramjet engine) to achieve maximum performance. The optimization of such criteria as thermal efficiency, specific output, and total performance for gas turbine engines, and overall efficiency, nondimensional thrust, and specific impulse for aero-engines has been performed by the optimization procedure with the multiplier method. Comparison of results with analytical solutions establishes the validity of the optimization procedure.

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