Evaluating the thermal fatigue strength of full-scale gas-turbine-engine blades

1983 ◽  
Vol 15 (7) ◽  
pp. 901-904
Author(s):  
M. E. Kolotnikov ◽  
S. Yu. Strilets
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Thermal Fatigue ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Turbine Engine ◽  
Thermal Fatigue Strength

Thermal fatigue of gas-turbine-engine blades made of a material based on silicon nitride and carbide

1983 ◽  
Vol 15 (7) ◽  
pp. 894-897 ◽  
Author(s):  
G. N. Tret'yachenko ◽  
B. S. Karpinos ◽  
B. D. Kosov
Keyword(s):  
Silicon Nitride ◽  
Gas Turbine ◽  
Thermal Fatigue ◽  
Gas Turbine Engine ◽  
Turbine Engine

Efficiency of process methods for improving the surface quality and fatigue strength of gas-turbine engine disks of the KhN73MBTYu-VD alloy

1998 ◽  
Vol 30 (5) ◽  
pp. 551-555
Author(s):  
V. A. Boguslayev ◽  
V. K. Yatsenko ◽  
A. G. Sakhno ◽  
N. V. Gonchar
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Surface Quality ◽  
Gas Turbine Engine ◽  
Turbine Engine

Effect of ultrasonic treatment on the fatigue strength of gas-turbine engine blades

1980 ◽  
Vol 12 (5) ◽  
pp. 570-572
Author(s):  
M. I. Evstigneev ◽  
A. M. Sulima ◽  
L. A. Fedorov
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Ultrasonic Treatment ◽  
Gas Turbine Engine ◽  
Turbine Engine

scholarly journals Thermal Fatigue Strength of Gas Turbine Rotor Disc

1962 ◽  
Vol 11 (102) ◽  
pp. 191-195
Author(s):  
Masaru KINOSHITA ◽  
Hidekazu YAMANOUCHI ◽  
Tetsuo IKI ◽  
Akio HIZUME
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Thermal Fatigue ◽  
Turbine Rotor ◽  
Thermal Fatigue Strength

scholarly journals Advances in Nonlinear Dynamic Engine Simulation With an Example: Dynamic Performance Behavior of a Gas Turbine With One Reheat Turbine Stage and Two Combustion Chambers

1996 ◽  
Author(s):  
M. T. Schobeiri ◽  
M. S. Attia
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Dynamic Simulation ◽  
Nonlinear Dynamic ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Turbine Stage ◽  
Combustion Chambers ◽  
Turbine Engine ◽  
Engine Simulation

The paper discusses some recent advances in dynamic engine simulation technology. A brief presentation of the physical background is followed by a detailed description of the turbine component, its modular representation, and its integration into the nonlinear dynamic engine simulation code GETRAN. In order to ensure the capability, accuracy, robustness, and reliability of the turbine module in interaction with GETRAN, comprehensive critical performance assessment and validation tests were performed. Two conceptually different engine configurations were dynamically simulated and their transient behavior was analyzed and compared with each other. As the first example, a full scale dynamic simulation of an advanced high performance single spool single shaft power generation gas turbine engine is presented. The second example includes the full scale dynamic simulation of an advanced power generation gas turbine engine with a reheat turbine stage and two combustion chambers. The comparison of these engines shows clearly the impact of the dynamic operation on the performance of individual gas turbine engines under consideration.

Fatigue strength of gas turbine engine rotor blades in connection with structural changes in service

1981 ◽  
Vol 16 (3) ◽  
pp. 282-284
Author(s):  
O. I. Marusii ◽  
B. A. Gryaznov ◽  
I. A. Makovetskaya
Keyword(s):  
Fatigue Strength ◽  
Gas Turbine ◽  
Structural Changes ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Turbine Engine ◽  
Engine Rotor

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.

scholarly journals Developments in New Gas Turbine Engine Demonstrator Programs

1986 ◽  
Author(s):  
Edward T. Johnson ◽  
David D. Klassen
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Full Scale ◽  
Lessons Learned ◽  
Turbine Engine ◽  
Applied Technology ◽  
Technology Level ◽  
Engine Development ◽  
Technology Demonstrator

Since 1967 the Aviation Applied Technology Directorate (AATD) has sponsored four technology demonstrator engine programs. These programs have been established for purposes of verifying the engine technology level appropriate for the initiation of full scale engine development. While these were all highly successful, significant improvements have evolved in the approach to these programs. This paper discusses this evolution, lessons learned, and results.

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