Defining and Measuring Factors Affecting Helicopter Turbine Engine Power Available

2021 ◽  
Author(s):  
Keyword(s):  
Turbine Engine ◽  
Factors Affecting ◽  
Engine Power

Estimation of the Hydraulic Losses in the Work Shaft of a Gas Turbine Engine of a Gas Compressor Unit Under Various Operating Conditions

2019 ◽  
Author(s):  
Oleg Baturin ◽  
Aleksandr Krivtsov ◽  
Daria Kolmakova ◽  
Grigorii Popov
Keyword(s):  
Complex Shape ◽  
Operating Conditions ◽  
Compressor Unit ◽  
Fuel Gas ◽  
Turbine Engine ◽  
Hydraulic Losses ◽  
Flow Through ◽  
Filter Unit ◽  
Research Recommendations ◽  
Engine Power

Abstract The paper presents the results of numerical simulation of air flow through a modernized variant of the inlet filter unit (IFU) of the gas compressor unit GPA-Ts-16. A feature of the IFU design is that to reduce the load on the filter unit, it is proposed to be as compact as possible, which determines its complex shape. The goal of the study is to study the hydraulic losses and to develop the measures to reduce them, since it is found that every 100 Pa of losses in the inlet unit increases the consumption of fuel gas by 2.5 kg/h or reduces the engine power by 10.5 kW. Calculations of hydraulic losses in IFU are carried out for cases of absence or presence of wind with a velocity from 0 to 35 m/s, blowing from 5 main directions (0°, 45°, 90°, 135°, 180°). Studies are also carried out on the effect of the weather shield shape, presence of baffles under it, and the rack in the shaft on the hydraulic losses. As a result of the research, recommendations are provided for designing (changing the shape) of the inlet filter unit that eventually allow to propose a design that will reduce the hydraulic losses in IFU by 15% relative to the originally suggested variant.

Performance Deterioration in Industrial Gas Turbines

1992 ◽  
Vol 114 (2) ◽  
pp. 161-168 ◽  
Author(s):  
I. S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

scholarly journals Justifications for an All-Radial 1600-HP Gas Turbine Engine

1970 ◽  
Author(s):  
R. J. Mowill
Keyword(s):  
Gas Turbine ◽  
Low Cost ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Engine Development

The philosophy and justifications behind a large all-radial single-shaft gas turbine engine development are discussed. In addition, some of the factors affecting the marketing of a simple and low cost engine are dealt with.

Performance Deterioration in Industrial Gas Turbines

1991 ◽  
Author(s):  
Ihor S. Diakunchak
Keyword(s):  
Gas Turbine ◽  
Service Time ◽  
Gas Turbines ◽  
Engine Performance ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Preventative Measures ◽  
Industrial Gas Turbines ◽  
Performance Deterioration ◽  
Industrial Gas Turbine

This paper describes the most important factors affecting the industrial gas turbine engine performance deterioration with service time and provides some approximate data on the prediction of the rate of deterioration. Recommendations are made on how to detect and monitor the performance deterioration. Preventative measures, which can be taken to avoid or retard the performance deterioration, are described in some detail.

scholarly journals Life Prediction for the Main Shaft of Aircraft Turbine Engine

1985 ◽  
Author(s):  
Liu Dunhui
Keyword(s):  
Fatigue Life ◽  
Life Prediction ◽  
Block Diagram ◽  
Local Stress ◽  
Design Stage ◽  
Main Shaft ◽  
Turbine Engine ◽  
Factors Affecting ◽  
Testing Method ◽  
Main Factor

The life prediction of the main shaft is described herein at the following three aspects: estimation of the fatigue life, testing method of the fatigue life and determination method of the service life for the main shaft. Based on the working practice, a working block diagram of life determinating procedure for the main shaft, from which the prediction contents and steps of the fatigue life for the main shaft can be seen, is also included in this paper. Since the factors affecting the fatigue life of hardwares are very complicated, so only the main factor can be taken into consideration in the method of prediction of the life. Therefore, in this paper it is emphasized to establish a life prediction computation program which integrates the main shaft design, testing and application, so that the computation theory of the whole life prediction can be established on the foundation of the test practice and service experience. The life of main shaft can be predicted by calculation during the design stage. The local stress method and strain empiric formula are applicable for the prediction of the main shaft life in its elastoplastic area.

scholarly journals ANALYSIS OF THE OPERATING LOAD OF THE TURBINE ENGINE DURING DECELERATION TO DASH MANEUVER

2016 ◽  
Vol 2 (1) ◽  
pp. 66-72
Author(s):  
Zbigniew Czyż
Keyword(s):  
Least Squares ◽  
Least Squares Method ◽  
Unmanned Helicopter ◽  
Gas Generator ◽  
Turbine Engine ◽  
Operating Load ◽  
Acceleration And Deceleration ◽  
Bearing Assembly ◽  
Velocity Changes ◽  
Engine Power

The article presents the analysis of the loads on the gas generator of turbine engine power of unmanned helicopter. The analysis was performed for deceleration to dash maneuver. Particular attention was paid to loads of bearing assembly in gas generator of turbine engine. The analysis was based on the timelines of changes in velocity of manned helicopter PZL W3-Falcon. The dependence of velocity changes during the flight was made as approximation by the least squares method and then determined for its change in acceleration. On this basis, the forces acting on the bearing gas generator assembly in static and dynamic conditions were determined. These values were compared with values obtained during maneuvers such as "jump up and jump down" and "acceleration and deceleration maneuver".

Sign in / Sign up

Export Citation Format

Share Document