Dynamic stress state of blades of gas-turbine-engine turbocompressors

1985 ◽  
Vol 17 (3) ◽  
pp. 428-433
Author(s):  
V. M. Kapralov
Keyword(s):  
Stress State ◽  
Gas Turbine ◽  
Dynamic Stress ◽  
Gas Turbine Engine ◽  
Turbine Engine

scholarly journals Дослідження напруженого стану міжпазових виступів диска робочого колеса компресора з урахуванням впливу відцентрових сил та розладу частот коливань лопаток

2021 ◽  
pp. 47-54
Author(s):  
Анатолій Павлович Зіньковський ◽  
Вячеслав Михайлович Меркулов ◽  
Олег Леонідович Деркач ◽  
Іван Гордійович Токар ◽  
Кирило Валентинович Савченко
Keyword(s):  
Stress State ◽  
Gas Turbine ◽  
Numerical Experiments ◽  
Practical Importance ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Centrifugal Forces ◽  
Blade Vibration ◽  
Turbine Engine

The authors present the results of the numerical experiments on the determination of the effect of compressor blade mistuning on the stress state of a blade-disk joint under the action of the centrifugal forces and their comparison with results of full-scale experiments. The analysis of the results of the previously performed experimental and numerical experiments on the determination of the possible sources of blade-disk joints failure shows their stress state strongly depends on the disk rim thickness and the blade vibration mode and their mistuning. It indicates the need for further studies to determine the causes of cracks and possible fracture of blade-disk joints in the compressor of a gas-turbine engine. The task is solved in the variation of the dovetail-rim region thickness of the disk of the 1st stage of the low-pressure compressor of the gas-turbine engine D-36, which has blades without shrouds. The finite element models of the blade assembly, are used to perform the investigation. Obtained results of the vibration stress analysis of blade-disk joints in the compressor both modifications under the action of the centrifugal forces have good agreement with the data of full-scale experiments and numerical data using rod models. The presented results of the numerical experiments indicate the possibility of reducing vibration stresses by analyzing and choosing parameters that affect the rigidity of the coupling of the blades, which is of practical importance for increasing the vibration reliability of the compressors of gas-turbine engines.

Flexible manufacturing in repair of gas turbine engine components

1992 ◽  
Author(s):  
KIRK D ◽  
ANDREW VAVRECK ◽  
ERIC LITTLE ◽  
LESLIE JOHNSON ◽  
BRETT SAYLOR
Keyword(s):  
Gas Turbine ◽  
Flexible Manufacturing ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Components

Fracture of a Compressor Stator Blade in a Gas Turbine Engine

2013 ◽  
Vol 50 (1) ◽  
pp. 43-49
Author(s):  
A. Neidel ◽  
B. Matijasevic-Lux
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Stator Blade

Uncharacteristic Circumferential TMF Cracking in a Heavy-duty Stationary Gas Turbine Engine Burner Outlet

2015 ◽  
Vol 52 (6) ◽  
pp. 334-341
Author(s):  
A. Neidel ◽  
Th. Ullrich ◽  
S. Wallich
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Heavy Duty ◽  
Turbine Engine
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