Finite-element analysis of unsteady temperature fields in parts of gas turbine engines

1989 ◽  
Vol 21 (12) ◽  
pp. 1720-1726
Author(s):  
Yu. G. Ispolov ◽  
N. N. Shabrov
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Temperature Fields ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Element Analysis ◽  
Unsteady Temperature

Reducing the Time-to-Solution for Finite Element Analysis of Gas Turbine Engines

2019 ◽  
Author(s):  
Todd A. Simons ◽  
James Ong ◽  
Robert Lucas ◽  
François-Henry Rouet ◽  
Roger Grimes ◽  
...  
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Element Analysis

scholarly journals The Impact Load on Containment Rings During a Multiple Blade Shed in Aircraft Gas Turbine Engines

1991 ◽  
Author(s):  
T. B. Dewhurst
Keyword(s):  
Finite Element Analysis ◽  
Gas Turbine ◽  
Impact Load ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Complete Understanding ◽  
Element Analysis ◽  
Turbine Engine ◽  
Hoop Stresses ◽  
The Impact

In the event of a multiple blade shed in an aircraft gas turbine engine, the impact load upon the containment ring is critical. A complete understanding of this load is necessary to design optimal rings, which are strong enough to contain blade fragments without incurring excess weight penalties. In this study a description of a multiple blade shed and subsequent ring failure is given. A finite element analysis of actual engine experiments is then used to determine the impact load on containment rings during a multiple blade shed. The situation modeled here is one where the initial blade fragments are contained but subsequent blade failures create large hoop stresses that result in brittle tensile failures in the ring.

Application of the Software System of Finite Element Analysis for the Simulation and Design Optimization of Solar Photovoltaic Thermal Modules

2020 ◽  
pp. 106-131 ◽  
Author(s):  
Vladimir Panchenko ◽  
Sergey Chirskiy ◽  
Valeriy Vladimirovich Kharchenko
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Solar Cells ◽  
Heat Removal ◽  
Operating Conditions ◽  
Temperature Fields ◽  
Thermal Mode ◽  
Solar Photovoltaic ◽  
Element Analysis ◽  
Ansys System

The chapter discusses the simulation of thermal operating conditions and the optimization of the design of solar photovoltaic thermal modules. As a realization of the developed method, two photovoltaic thermal modules with one-sided solar cells with one-sided heat removal and two-sided solar cells with two-sided heat removal are presented. The components of the developed models of solar modules must be optimized on the basis of the required indicators of the thermal mode of operation of the modules. For this task, a method has been developed for visualizing thermal processes using the Ansys system of finite element analysis, which has been used to research thermal modes of operation and to optimize the design of the modules created. With the help of the developed method, the temperature fields of the module components, coolant velocity and its flow lines in the developed models of a planar photovoltaic thermal roofing panel and a concentrator photovoltaic thermal two-sided module are visualized.

scholarly journals Theoretical analysis of gas turbine blade by finite element method

1970 ◽  
Vol 9 (9) ◽  
pp. 29-33 ◽  
Author(s):  
B Deepanraj ◽  
P Lawrence ◽  
G Sankaranarayanan
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Temperature Distribution ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Optimum Number ◽  
Gas Turbine Blade ◽  
Element Analysis ◽  
Functional Part ◽  
Optimum Solution

Gas turbine is an important functional part of many applications. Cooling of blades has been a major concern since they are in a high temperature environment. Various techniques have been proposed for the cooling of blades and one such technique is to have axial holes along the blade span. Finite element analysis is used to analyze thermal and structural performance due to the loading condition, with material properties of Titanium- Aluminum Alloy. Six different models with different number of holes (7, 8, 9, 10, 11, and 12) were analyzed in this paper to find out the optimum number of holes for good performance. In Finite element analysis, first thermal analysis followed by structural analysis is carried out. Graphs are plotted for temperature distribution for existing design (12 holes) and for 8 holes against time. 2D and 3D model of the blade with cooling passages are shown. Using ANSYS, bending stress, deflection, temperature distribution for number of holes are analyzed. It is found that when the numbers of holes are increased in the blade, the temperature distribution falls down. For the blade configuration with 8 holes, the temperature near to the required value i.e., 800ºC is obtained. Thus a turbine blade with 8 holes configuration is found to be the optimum solution. Keywords: Gas turbine blade; Stress; Deflection; Temperature distribution. DOI: http://dx.doi.org/10.3126/sw.v9i9.5514 SW 2011; 9(9): 29-33

scholarly journals Assessment of Mechanical Design Parameters for an Aero Gas Turbine Engine Jet Pipe Casing using Finite Element Analysis

2020 ◽  
Vol 9 (5) ◽  
pp. 1197-1201
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Gas Turbine ◽  
Mechanical Design ◽  
Three Dimensional ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Element Analysis ◽  
Engine Operation ◽  
Turbine Engine

Aero Gas Turbine engines power aircrafts for civil transport application as well as for military fighter jets. Jet pipe casing assembly is one of the critical components of such an Aero Gas Turbine engine. The objective of the casing is to carry out the required aerodynamic performance with a simultaneous structural performance. The Jet pipe casing assembly located in the rear end of the engine would, in case of fighter jet, consist of an After Burner also called as reheater which is used for thrust augmentation to meet the critical additional thrust requirement as demanded by the combat environment in the war field. The combustion volume for the After burner operation together with the aerodynamic conditions in terms of pressure, temperature and optimum air velocity is provided by the Jet pipe casing. While meeting the aerodynamic requirements, the casing is also expected to meet the structural requirements. The casing carries a Convergent-Divergent Nozzle in the downstream side (at the rear end) and in the upstream side the casing is attached with a rear mount ring which is an interface between engine and the airframe. The mechanical design parameters involving Strength reserve factors, Fatigue Life, Natural Frequencies along with buckling strength margins are assessed while the Jet pipe casing delivers the aerodynamic outputs during the engine operation. A three dimensional non linear Finite Element analysis of the Jet pipe casing assembly is carried out, considering the up & down stream aerodynamics together with the mechanical boundary conditions in order to assess the Mechanical design parameters.

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]

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