General features of technological engineering of a gas turbine engine with function-based structure properties

General features of technological engineering of a gas turbine engine with function- based properties of structural elements that provide an increase in its resource under the conditions of uneven operational impacts are presented. A general methodology of technological engineering of a gas turbine engine with function-based properties formed on the basis of a complex multi-connected technological process has been developed. In furtherance of the general methodology of technological engineering of a gas turbine engine, an algorithm for its implementation using an iterative-recurrent approach has been developed.

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Modeling the Gas Turbine Engine Under Its Dynamic Heating Conditions

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.4028449 ◽

2014 ◽

Vol 137 (3) ◽

Cited By ~ 2

Author(s):

Sergiy V. Yepifanov ◽

Roman L. Zelenskyi ◽

Igor Loboda

Keyword(s):

Gas Turbine ◽

Mutual Effect ◽

Gas Turbine Engine ◽

Path Model ◽

Structural Elements ◽

Dynamics Model ◽

Unsteady Temperature ◽

Turbine Engine ◽

Operating Modes ◽

Dynamic Heating

A modern gas turbine engine (GTE) is a complex nonlinear dynamic system with the mutual effect of gas-dynamic and thermal processes in its components. The engine development requires the precise real-time simulation of all main operating modes. One of the most complex operating modes for modeling is “cold stabilization,” which is the rotors acceleration without completely heated up the turbine elements. The dynamic heating problem is a topical practical issue. Solving the problem requires coordinating a gas-path model with heat and stress models, which is also a significant scientific problem. The phenomenon of interest is the radial clearances change during engines operation and its influence on engines static and dynamic performances. To consider the clearance change, it is necessary to synthesize the quick proceeding stress-state models (QPSSM) of a rotor and a casing for the initial temperature and dynamic heating. The unique feature of the QPSSM of GTEs is separate equation sets, which allow the heat exchange between structure elements and the gas (air) and the displacements of the turbine rotor and the casing. This ability appears as a result of determining the effect of each factor on different structural elements of the engine. The presented method significantly simplifies the model identification, which can be performed based on a precise calculation of the unsteady temperature fields of the structural elements and the variation of the radial clearance. Thus, the present paper addresses a new method to model the engine dynamics considering its heating up. The method is based on the integration of three models: the gas-path dynamics model, the clearance dynamics model, and the model of the clearance effect on the efficiency. The paper also comprises the program implementation of the models. The method was tested by applying to a particular turbofan engine.

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Numerical simulation of gas flow in jet nozzle

Journal of «Almaz – Antey» Air and Defence Corporation ◽

10.38013/2542-0542-2016-3-41-46 ◽

2016 ◽

pp. 41-46

Author(s):

S. V. Skachkov ◽

D. D. Shpakovskiy

Keyword(s):

Numerical Simulation ◽

Gas Turbine ◽

Gas Flow ◽

Gas Turbine Engine ◽

Inlet Section ◽

Structural Elements ◽

Hydraulic Characteristics ◽

Turbine Engine ◽

Flow Swirl ◽

Jet Nozzle

We determined traction and hydraulic characteristics of the jet nozzle of a gas turbine engine, taking into account the geometry of the internal structural elements and flow swirl in the inlet section according to the results of numerical simulation.

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Structural reliability and methods for gas turbine engine life increase based on support of functionally-directed properties

Science intensive technologies in mechanical engineering ◽

10.12737/article_5a8ef9cf16dbd8.65103997 ◽

2018 ◽

Vol 2018 (3) ◽

pp. 32-41 ◽

Cited By ~ 2

Author(s):

А. Михайлов ◽

A. Mikhaylov ◽

В. Михайлов ◽

V. Mikhailov ◽

Д. Михайлов ◽

...

Keyword(s):

Gas Turbine ◽

Structural Reliability ◽

Aircraft Engine ◽

Gas Turbine Engine ◽

Structural Elements ◽

Basic Principles ◽

Turbine Engine ◽

Engine Design ◽

Element Base ◽

Engine Reliability

In the paper presented there is carried out an analysis of peculiarities in the operation of structural elements and subsystems of gas turbine engine (GTE). A GTE structural reliability is investigated which is defined at the stage of aircraft engine design. There are shown structural logistic formulae of aircraft engine reliability. In the work there is offered a general approach to the life increase of GTE structural elements on the basis of functionally-directed properties. Basic principles for the support of functionally-directed properties of the GTE element base are shown. The ways to ensure a specified rated or limit GTE life on the basis of functionally-directed properties of elements are shown.

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Prospects of application of additive technologies to develop parts and components of gas turbine engines and ramjets

VESTNIK of the Samara State Aerospace University ◽

10.18287/2541-7533-2019-18-3-81-98 ◽

2019 ◽

Vol 18 (3) ◽

pp. 81-98

Author(s):

L. A. Magerramova ◽

Yu. A. Nozhnitsky ◽

S. A. Volkov ◽

M. E. Volkov ◽

V. Zh. Chepurnov ◽

...

Keyword(s):

Combustion Chamber ◽

Gas Turbine ◽

Cooling System ◽

Experimental Studies ◽

Gas Turbine Engine ◽

Additive Technologies ◽

Cellular Structures ◽

Structural Elements ◽

Turbine Engine ◽

Wide Range

The possibility of reducing the weight, simplifying the design, reducing the time and cost of development, production and operation are important advantages in the implementation of additive technologies (AT). The use of AT can significantly improve fuel efficiency, environmental and other characteristics of aircraft engines. The possibility of using AT in the production of various parts and components of engines is being currently investigated at CIAM. Examples of these developments, advantages of the use of AT and problems arising in the implementation of these technologies are presented in this article. Models of turbine blades with a highly efficient cooling system, in particular, with penetration cooling were designed and manufactured using optimization methods and taking into account the capabilities of AT. The possibilities of using AT for the manufacture of elements of molds for precision casting of gas turbine engine (GTE) blades of heat-resistant alloys and ceramic rods are shown. Elements of a two-zone front module of the low-emission combustion chamber of an advanced GTE are designed and manufactured using the AT method. Research of prospective branched tree channels of heat exchangers with mutually porous bodies that can be made only by AT methods and the use of which will make it possible to increase the efficiency of heat exchange in the case of lower weight, than that of the structures made by traditional technologies, is being carried out. The AT was used to manufacture complex elements of a ramjet engine. Fire tests of printed sections of the combustion chamber were carried out successfully. Cellular structures to be used in gas turbine engine parts with the aim of reducing their weight were developed. A hollow blade model with cellular-type core was made using AT. Tests of the designed cellular prototypes were carried out. The possibilities of reducing the mass of structural elements using cellular structures obtained by AT methods are shown. Research of hollow disks of turbines and other engine components produced with the aid of AT are carried out. Despite the fact that experimental studies of structural elements obtained by additive technologies have not been completed yet, these works show the prospects for the use of AT in the development of a wide range of engine parts and components.

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