scholarly journals Performance simulation of multi-stage axial-flow compressor of turbo-shaft engine with account for erosive wear nonlinearity of its blades

2020 ◽  
Vol 23 (5) ◽  
pp. 39-53
Author(s):  
V. A. Potapov ◽  
A. A. Sanko
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Axial Flow Compressor ◽  
Multi Stage ◽  
Rotor Wing ◽  
Flow Compressor

The construction and useful practice of gas-turbine engine diagnosis systems depend largely on the availability of the engine mathematical models and its certain components in their structure. Utilization of multi-stage axial flow compressor performance with account for erosive wear of its parts during the operation fundamentally raises possibilities of such systems as erosive wear of flow channel, blade rings of impellers and vane rings of multi-stage compressor is a common cause of preschedule gas-turbine engine detaching from an aircraft. As evidenced by various contributions presented in the article, special emphasis on abrasive wear impact assessment on axial flow compressor performance is placed upon rotor-wing turbo-shaft engine due to their particular operating conditions. One of the main tasks in the process of mathematic simulation of an axial flow compressor blade ring is consideration of its wear type that again has a nonlinear distribution along the level of the blade. In addition, wear rate at entry and exit blade edges often have different principles. Detecting of these principles and their consideration when constructing the compressor mathematical model is a crucial task in diagnostic assessment and integrity monitoring of rotor-wing turbo-shaft engine in operation. The article represents a concept to an estimate nonlinear erosive wear effect of axial flow compressor blades on its performance based on the three-dimensional flow approach in the gas-air flow duct of compressor with a formulation of the blade rings. This approach renders possible to take into account the nonlinearity of the compressor blades wear during their operation. Through the example of the inlet compressor stage of a rotor-wing aircraft gas-turbine engine, the engine pump properties predictions with different kind of rotor blade wear have been presented.

scholarly journals Optimum Control of Variable Components in Aircraft Gas Turbine Engines Under Non-Stationary Flow Disturbances at the Inlet

1994 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kreitinin
Keyword(s):  
Gas Turbine ◽  
Dynamic Control ◽  
Axial Flow ◽  
Stationary Flow ◽  
Turbine Engines ◽  
Stable Operation ◽  
Turbine Engine ◽  
Axial Flow Compressor ◽  
Flow Disturbances ◽  
Flow Compressor

A numerical method has been preposed to determine optimum laws to control gas turbine engine (CTE) variable components, including an independent control of blade rows in a multistage axial flow compressor under strong non-stationary flow disturbances at the inlet, optimum laws to control a turbofan under non-stationary thermal effects at the inlet have been obtained using mathematical models with various degree of filling in detail the flow in an engine flow path. There is shown a possibility to considerably increase a range of the CTE stable operation through the use of dynamic control of stator blades in a multistage axial flow compressor, also possibilities of practical use of optimum laws to control engine variable components in the system of preventing an unstable operation are being discussed.

Optimization of Gas Turbine Engine Elements by Probability Criteria

1993 ◽  
Author(s):  
I. N. Egorov ◽  
G. V. Kretinin
Keyword(s):  
Stochastic Optimization ◽  
Gas Turbine ◽  
Axial Flow ◽  
Gas Turbine Engine ◽  
Design Parameters ◽  
Technical Object ◽  
Turbine Engine ◽  
Flow Compressor ◽  
Engine Components ◽  
Stochastic Setting

Procedure for the stochastic optimization of design parameters of gas turbine engine components for a prescribed level of production technology is discussed. Such combined criteria of the stochastic optimization as effectiveness-probability of realizing a design of an intricate technical object are proposed. With reference to the task of optimum designing the rows of a multistage axial flow compressor, there are presented the results, obtained for various probability criteria, in parallel with conducting their comparative analysis, and there are also investigated optimum stable (robust) characteristics of designs obtained for various levels of technology. There are also demonstrated a possibility of a significant increase in probability to realize in actual practice the design, obtained in stochastic setting, as compared to the design, obtained in deterministic setting.

Influence of Secondary Inertia Terms on Natural Frequencies of Rotating Beams

1955 ◽  
Vol 22 (4) ◽  
pp. 587-591
Author(s):  
J. L. Bogdanoff
Keyword(s):  
Gas Turbine ◽  
Cantilever Beam ◽  
Natural Frequencies ◽  
Axial Flow ◽  
Rotating Disk ◽  
Compressor Blades ◽  
Disk Radius ◽  
Small Motion ◽  
Axial Flow Compressor ◽  
Flow Compressor

Abstract The equations of small motion of a straight cantilever beam attached to the rim of a rotating disk are determined assuming the Bernoulli-Euler theory of bending and the Saint Venant theory of torsion are valid, the mass and elastic axes coinciding and retaining all inertia terms. Influence of the secondary inertia terms on the fundamental torsional and lateral frequencies is then examined at two angular settings for a uniform beam having a length to disk-radius ratio in the range usually encountered in gas-turbine buckets and axial-flow compressor blades.

scholarly journals Dependence of thermogasodynamic parameters of operation of a helicopter gas turbine engine on its operation and dust in the atmosphere

2021 ◽  
Vol 66 (3) ◽  
pp. 307-319
Author(s):  
V. A. Potapov ◽  
A. A. Sanko ◽  
M. V. Kudin
Keyword(s):  
Gas Turbine ◽  
Stokes Equations ◽  
Block Diagram ◽  
Operating Time ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Gas Turbine Compressor

By scanning the blades of the impeller and the guide devices of the full-scale compressor of the helicopter gas turbine engine, a solid-state design model of the compressor with a tunable geometry in the height of the blades was developed. The empirical dependencies of the values of nonlinear wear of the blade of the 1st stage of the compressor on the operating time and the concentration of dust in the air are presented. A block diagram of the procedure for calculating the characteristics and parameters of a helicopter gas turbine compressor is presented. When calculating the flow in the gas–air path of the compressor, the numerical solution of the Navier–Stokes equations averaged by Reynolds, the finite element method in combination with the establishment of patterns of erosive wear of the blades depending on the operating conditions of the engine is used. Mathematical dependencies of the thermogasodynamic parameters of the helicopter gas turbine compressor operation on its operating time and the dustiness of the atmosphere are obtained using modeling. The obtained results can be used in the development of a methodology for automated monitoring of the wear condition of the compressor blades of a helicopter gas turbine engine according to its thermogasodynamic parameters, applied to various climatic operating conditions.

Extrapolation of Compressor Characteristics to the Low-Speed Region for Sub-Idle Performance Modelling

2002 ◽  
Author(s):  
Geoff Jones ◽  
Pericles Pilidis ◽  
Barry Curnock
Keyword(s):  
Gas Turbine ◽  
Axial Flow ◽  
Extrapolation Methods ◽  
Performance Modelling ◽  
Turbine Engine ◽  
Low Speed ◽  
Axial Flow Compressor ◽  
Design Values ◽  
High Flows ◽  
Flow Compressor

In order to model the performance of a gas-turbine engine in the sub-idle region, particularly for starting and windmilling, it is necessary to use compressor characteristics which describe their operation and low speeds. As most compressor tests are conducted only in the range of operating speeds normally encountered, the resultant characteristics must be extrapolated in order to define the low speed compressor maps. In this paper, a variety of techniques for the extrapolation of axial-flow compressor characteristics are presented and evaluated. These include those presented by De-You & Zhong-Fan [4], Agrawal & Yunis [1] and Converse & Giffen [3]. The ease and reliability of the extrapolation methods are compared. Problems associated with the prediction of losses within the turbomachinery are highlighted, particularly in respect of compressor operation at high flows and low rotational speeds. This is due to the creation of highly off-design values of incidence which are not encountered during above-idle running, but which may be found during windmilling.

Development and Testing of Polyurethane Coating for Protection of Gas Turbine Engine Blades

2021 ◽  
Vol 316 ◽  
pp. 868-872
Author(s):  
Maksim A. Orlov ◽  
Irina A. Polikarpova ◽  
Aleksander N. Kalinnikov
Keyword(s):  
Gas Turbine ◽  
Protective Coating ◽  
Erosive Wear ◽  
Gas Turbine Engine ◽  
Polyurethane Coating ◽  
State Technical ◽  
Turbine Engine ◽  
Temperature Resistance ◽  
Technical University

The article presents testing of polymer protective coating based on polyurethane developed in Bauman Moscow State Technical University. It is shown that the developed coating has an increased resistance to erosive wear, an increased level of adhesion and temperature resistance, compared with the existing coatings, certified by aviation.

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