Effect of long service on the fine structure of the surface of gas turbine engine rotor blades

1977 ◽  
Vol 9 (10) ◽  
pp. 1257-1261
Author(s):  
O. I. Marusii ◽  
Yu. I. Koval' ◽  
E. N. Kaspruk ◽  
V. N. Torgov
Keyword(s):  
Fine Structure ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Turbine Engine ◽  
Engine Rotor

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

Full-Annulus URANS Study on the Transportation of Combustion Inhomogeneity in a Four-Stage Cooled Turbine

2019 ◽  
Author(s):  
Zhongran Chi ◽  
Haiqing Liu ◽  
Shusheng Zang ◽  
Chengxiong Pan ◽  
Guangyun Jiao
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Inlet Temperature ◽  
Computational Domain ◽  
Temperature Inhomogeneity ◽  
Unsteady Temperature ◽  
Turbine Engine ◽  
Exhaust Temperature ◽  
The Time Domain

Abstract The inhomogeneity of temperature in a turbine is related to the nonuniform heat release and air injections in combustors. In addition, it is influenced by the interactions between turbine cascades and coolant injections. Temperature inhomogeneity results in nonuniform flow temperature at turbine outlets, which is commonly measured by multiple thermal couples arranged in the azimuthal direction to monitor the operation of a gas turbine engine. Therefore, the investigation of temperature inhomogeneity transportation in a multistage gas turbine should help in detecting and quantifying the over-temperature or flameout of combustors using turbine exhaust temperature. Here the transportation of temperature inhomogeneity inside the four-stage turbine of a 300-MW gas turbine engine was numerically investigated using 3D CFD. The computational domain included all four stages of the turbine, consisting of more than 500 blades and vanes. Realistic components (N2, O2, CO2, and H2O) with variable heat capacities were considered for hot gas and cooling air. Coolants were added to the computational domain through more than 19,000 mass and momentum source terms. his was simple compared to realistic cooling structures. A URANS CFD run with over-temperature/flameout at 6 selected combustors out of 24 was carried out. The temperature distributions at rotor–stator interfaces and the turbine outlet were quantified and characterized by Fourier transformations in the time domain and space domain. It is found that the transport process from the hot-streaks/cold-streaks at the inlet to the outlet is relatively stable. The cold and hot fluid is redistributed in time and space due to the stator and rotor blades, in the region with a large parameter gradient at the inlet, strong unsteady temperature field and composition field appear. The distribution of the exhaust gas composition has a stronger correlation with the inlet temperature distribution and is less susceptible to interference.

Three-Dimensional Structural Evaluation of a Gas Turbine Engine Rotor

2014 ◽  
Author(s):  
Partha S. Das
Keyword(s):  
Finite Element ◽  
Steady State ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Complex Geometries ◽  
Turbine Engine ◽  
Industrial Gas Turbine ◽  
Engine Rotor ◽  
Engine Rotors ◽  
Critical Locations

Engine rotors are one of the most critical components of a heavy duty industrial gas turbine engine, as it transfers mechanical energy from rotor blades to a generator for the production of electrical energy. In general, these are larger bolted rotors with complex geometries, which make analytical modeling of the rotor to determine its static, transient or dynamic behaviors difficult. For this purpose, powerful numerical analysis approaches, such as, the finite element method, in conjunction with high performance computers are being used to analyze the current rotor systems. The complexity in modeling bolted rotor behavior under various loadings, such as, airfoil, centrifugal and gravity loadings, including engine induced vibration is one of the main challenges of simulating the structural performance of an engine rotor. In addition, the internal structural temperature gradients that can be encountered in the transient state as a result of start-up and shutdown procedures are generally higher than those that occur in the steady-state and hence thermal shock is important factor to be considered relative to ordinary thermal stress. To address these issues, the current paper presents the steady-state & quasi-static analyses (to approximate transient responses) of two full 3-D industrial gas turbine engine rotors, SW501F & GE-7FA rotor, comprising of both compressor & turbine sections together. Full 3-D rotor analysis was carried out, since the 2-D axisymmetric model is inadequate to capture the complex geometries & out of plane behavior of the rotor. Both non-linear steady-state & transient analyses of a full gas turbine engine rotor was performed using the general purpose finite element analysis program ABAQUS. The paper presents in detail the FEA modeling technique, overall behavior of the full rotor under various loadings, as well as, the critical locations in the rotor with respect to its strength and life. The identification of these critical locations is needed to help with the repair of the existing rotors and to improve and extend the operational/service life of these rotors.

Rational Design of Gas Turbine Engine Compressor to Provide the Required Dynamic Strength Level of Rotor Blades

2016 ◽  
Author(s):  
Daria Kolmakova ◽  
Grigorii Popov ◽  
Aleksandr Shklovets ◽  
Aleksandr Ermakov
Keyword(s):  
Gas Turbine ◽  
Rational Design ◽  
Gas Flow ◽  
Dynamic Strength ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Dynamic Stresses ◽  
Turbine Engine ◽  
Acceptable Method ◽  
Flow Oscillations

Compressors of gas turbine engines often operate under the conditions of uneven gas flow. Oscillations of the blades occur under the influence of circumferential flow unevenness. The goal of the research was to find an acceptable method of reducing the level of dynamic stresses in the rotor blades. Motivation for the study was the problem of destruction of rotor blades of the last stage of Intermediate Pressure Compressor (IPC) which has been designed and produced at JSC “Kuznetsov” (Russia). The source of circumferential flow unevenness was middle annular frame located downstream the IPC. Seven struts with different maximum thickness are arranged irregularly in support passage. The first approaches propose to reduce the dynamic stresses in blades by detuning the blades from the dangerous harmonic due to changes in their natural frequency. The next two consist in reducing the circumferential unevenness of flow. Thus, this study gives the ideas about methods of improving the dynamic strength of rotor blades of gas turbine engine compressors. On the basis of existing conditions (under development or existing compressor) it allows the selection of the most suitable method for reducing dynamic stresses.

Optimization of a Gas Turbine Engine Rotor Disc Using Case-Based Reasoning and the GATE Genetic Algorithm

2010 ◽  
Author(s):  
S. Dominique ◽  
J.-Y. Tre´panier
Keyword(s):  
Genetic Algorithm ◽  
Gas Turbine ◽  
Structural Design ◽  
Gas Turbine Engine ◽  
Pattern Search ◽  
Case Based Reasoning ◽  
Turbine Engine ◽  
Local Searches ◽  
Case Based ◽  
Engine Rotor

The implementation of an automated decision support system in the field of structural design and optimization can give a significant advantage to any industry working on mechanical design. Such a system can reduce the project cycle time or allow more time to produce a better design by providing solution ideas to a designer or by upgrading existing design solutions while the designer is not at work. This paper presents an approach to automating the process of designing a gas turbine engine rotor disc using case-based reasoning (CBR), combined with a new genetic algorithm, the Genetic Algorithm with Territorial core Evolution (GATE). GATE was specifically created to solve problems in the mechanical structural design field, and is essentially a real number genetic algorithm that prevents new individuals from being born too close to previously evaluated solutions. The restricted area becomes smaller or larger during optimization to allow global or local searches when necessary. The CBR process uses a databank filled with every known solution to similar design problems. The closest solutions to the current problem in terms of specifications are selected, along with an estimated solution from an artificial neural network. Each solution selected by the CBR is then used to initialize the population of a GATE island. Our results show that CBR may significantly upgrade the performance of an optimization algorithm when sufficient preliminary information is known about the design problem. It provides an average solution 5.0% lighter than the average solution found using random initialization. The results are compared to other results obtained for the same problems by four optimization algorithms from the I-SIGHT 3.5 software: the sequential quadratic programming algorithm (SQP), the insular genetic algorithm (GA), the Hookes & Jeeves generalized pattern search (HJ) and POINTER. Results show that GATE can be a very good candidate for automating and accelerating the structural design of a gas turbine engine rotor disc, providing an average disc 18.9% lighter than SQP, 11.2% lighter than HJ, 23.9% lighter than GA and 4.3% lighter than POINTER, even when starting with the same solution set.

Vibration based damage detection of rotor blades in a gas turbine engine

2014 ◽  
Vol 46 ◽  
pp. 26-39 ◽  
Author(s):  
S. Madhavan ◽  
Rajeev Jain ◽  
C. Sujatha ◽  
A.S. Sekhar
Keyword(s):  
Damage Detection ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Rotor Blades ◽  
Turbine Engine
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