STATIC TESTS OF FULL-SIZE ACOUSTIC PANELS OF AIRCRAFT GAS-TURBINE ENGINES

Kontrol Diagnostika ◽

10.14489/td.2020.08.pp.018-023 ◽

2020 ◽

pp. 18-23

Author(s):

N. V. Osadchy ◽

V. T. Shepel

Keyword(s):

Finite Element ◽

Gas Turbine ◽

Flaw Detection ◽

Static Strength ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Safe Operation ◽

Static Tests ◽

Finite Element Calculations ◽

Comparison Of The Results

The article suggests the installation and methods of static tests for the limit working and fracture loads of acoustic panels of aircraft gas-turbine engines (GTE). It is not possible to perform the full scope of static tests on the engine as it is technically impossible to obtain the airflow pressures required by airworthiness standards. The required pressure in the proposed installation is created by the punch, which is the same shape as the panel to be tested. Flexible rubber sheets are used to equalize contact pressure on the panel surface. The similarity in the distribution of pressures on the surface of the acoustic panel created by the air flow as part of the GTE and the pressures created by the punch as part of the installation is confirmed by comparing the stresses and deformations obtained as a result of finite-element calculations. The article presents the results of certification static tests and flaw detection of a three-layer acoustic panel. Comparison of the results of finite-element calculations of stresses and displacements of the acoustic panel as a part of GTE and as a part of the installation has shown that in the latter case the estimations of static strength are conservative, which positively affects their safe operation.

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Calculating blades of gas-turbine engines by the finite element method

Strength of Materials ◽

10.1007/bf01528130 ◽

1976 ◽

Vol 8 (6) ◽

pp. 683-688

Author(s):

A. L. Kvitka ◽

P. P. Voroshko ◽

L. A. Zaslotskaya

Keyword(s):

Finite Element Method ◽

Finite Element ◽

Gas Turbine ◽

Turbine Engines ◽

Gas Turbine Engines ◽

The Finite Element Method ◽

Element Method

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МОДЕЛИРОВАНИE ПРОЦЕССА ГОРЕНИЯ В ФАКЕЛЬНЫХ ВОСПЛАМЕНИТЕЛЯХ ГТД

Aerospace technic and technology ◽

10.32620/aktt.2019.7.05 ◽

2019 ◽

pp. 39-49

Author(s):

Юрий Иванович Торба ◽

Сергей Игоревич Планковский ◽

Олег Валерьевич Трифонов ◽

Евгений Владимирович Цегельник ◽

Дмитрий Викторович Павленко

Keyword(s):

Finite Element ◽

Boundary Conditions ◽

Computational Model ◽

Gas Turbine ◽

Test Bench ◽

Combustion Process ◽

Turbine Engines ◽

Combustion Model ◽

Gas Turbine Engines ◽

Turbine Engine

The aim of the work was the development and testing of methods for modeling the combustion process in the torch igniters of gas turbine engines. To achieve it, the finite element method was used. The main results of the work are the substantiation of the need to optimize the torch igniters of gas turbine engines. The practice of operating torch igniters of various designs has shown that the stability of their work depends on the parameters of gas turbine engines and external factors (air and fuel temperature, size of fuel droplets, fuel and air consumption, as well as its pressure). At the same time, the scaling of the geometry of the igniter design does not ensure its satisfactory work in the composition of the GTE with modified parameters. In this regard, an urgent task is to develop a combustion model in a flare igniter to optimize its design. A computational model of a torch igniter for a gas turbine engine of a serial gas-turbine engine in a software package for numerical three-dimensional thermodynamic simulation of AN-SYS FLUENT has been developed. To reduce the calculation time and the size of the finite element model, recommendations on the adaptation of the geometric model of the igniter for numerical modeling are proposed. The mod-els of flow turbulence and combustion, as well as initial and boundary conditions, are selected and substantiated. Verification of the calculation results obtained by comparison of numerical simulation with the data of tests on a specialized test bench was performed. It is shown that the developed computational model makes it possible to simulate the working process in the torch igniters of the GTE combustion chambers of the investigated design with a high degree of confidence. The scientific novelty of the work consists in substantiating the choice of the combustion model, the turbulence model, as well as the initial and boundary conditions that provide adequate results to the full-scale experiment on a special test bench. The developed method of modeling the combustion process in gas turbine torch igniters can be effectively used to optimize the design of igniters based on GTE operation conditions, as well as combustion initialization devices to expand the range of stable operation of the combustion chamber.

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

Strength of Materials ◽

10.1007/bf01533417 ◽

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

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Mechanics Modeling of Blade/Disk Contacts

World Tribology Congress III, Volume 1 ◽

10.1115/wtc2005-63545 ◽

2005 ◽

Author(s):

Matthew C. Gean ◽

Thomas N. Farris

Keyword(s):

Finite Element ◽

Singular Integral ◽

Singular Integral Equations ◽

Contact Stresses ◽

Turbine Engines ◽

Gas Turbine Engines ◽

Contact Loads ◽

Finite Element Calculations ◽

Normal And Tangential Loads ◽

Empirical Constants

A predictive procedure capable of calculating dovetail surface contact loads in gas turbine engines is developed. The procedure determines contact normal and tangential loads, for a complete mission involving radial blade and thermal loads. Once Finite Element calculations to determine empirical constants for a specific blade/disk geometry are completed, the predictive procedure handles complicated load histories in near real-time for both single and double tang dovetails. The resulting load histories can be combined with Singular Integral Equations to calculate edge-of-contact stresses. The resulting contact stresses have been used to successfully predict fretting fatigue lives under controlled laboratory conditions.

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