scholarly journals The Impact of Damage to the Compressor on the Operating Parameters of the Pratt & Whitney 206B2 Turbine Engine

2018 ◽  
Vol 9 (1) ◽  
pp. 61-78 ◽  
Author(s):  
Bartosz PRZYBYŁA ◽  
Zbigniew ZAPAŁOWICZ
Keyword(s):  
Cross Sections ◽  
Foreign Bodies ◽  
Rotation Speed ◽  
Gas Temperature ◽  
Engine Operation ◽  
Turbine Engine ◽  
Fuel Flow ◽  
Operating Medium ◽  
Turbine Shaft ◽  
The Impact

The article presents the impact of damage to the centrifugal compressor of the P&W 206B2 turbine engine, built in the EC-135p2 helicopters EC-135p2. The damages are caused by sucking the foreign bodies to the inlet, what results in the changes of exploitation parameters of the engine and thermodynamic parameters of operating medium. On the basis of the parameters, measured during engine operation, such as: rotation speed of the rotor of the compressor – n1, the rotation speed of the turbine shaft of the drive – n2, the gas temperature at the outlet of the turbine driving of the compressor – T4.2, and the fuel flow rate - m ̇_p, distributions of these parameters in various cross- sections of the engine were determined and compared. Then, on their basis, the CFD analysis of air flows in new and damaged compressors was performed.

A Method to Compare Turbine Engine Airstart Times

2007 ◽  
Author(s):  
Wade Casey ◽  
Donald Malloy ◽  
Steve Arnold ◽  
Gregory Shaff ◽  
David Kidman
Keyword(s):  
Analytical Approach ◽  
Simulation Test ◽  
Engine Operation ◽  
Turbofan Engine ◽  
Turbine Engine ◽  
Power Extraction ◽  
Installation Effects ◽  
Fuel Flow ◽  
Starter Motor ◽  
The Difference

Turbine engine airstarts are conducted throughout the aircraft airspeed/altitude envelope in ground-based simulation test facilities and in flight tests to ensure safe and reliable engine operation. Differences in airstart times are attributable to variations in engine turnaround speed (the engine core speed at which the airstart is initiated in spooldown airstarts); combustor lightoff time; installation effects such as customer bleed and power extraction; starter motor torque; fuel flow scheduling; and engine-to-engine variation and degradation. An analytical approach is presented to account for these differences and adjust engine airstart time for a low-bypass, twin-spool, military, turbofan engine. Two examples are presented illustrating the difference in airstart times and the analytical approach used to adjust the start times.

scholarly journals Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data

2018 ◽  
Vol 2018 ◽  
pp. 1-12 ◽  
Author(s):  
Mustagime Tülin Yildirim ◽  
Bülent Kurt
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Gas Turbine Engine ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Fuel Flow ◽  
The Status ◽  
Performance Deterioration ◽  
Artificial Neural Network Ann

Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.

scholarly journals Comparative Analysis of Gas Turbine Engine Starting

1998 ◽  
Author(s):  
Asfaw Beyene ◽  
Terry Fredlund
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Hydraulic Systems ◽  
Engine Operation ◽  
Turbine Engine ◽  
Hot Start ◽  
Service Areas ◽  
Control Procedures ◽  
Starting Characteristics ◽  
The Impact

Electric, pneumatic, combustion, and hydraulic systems are commonly used as gas turbine engine starters. All such starters must allow full-load engine operation to be reached within few or several minutes, depending on the size and type of the engine. This contrast in the power source of these starters imposes a variation in their operations including control procedures and safety measures such as blow-downs and on/off sequences. Driving characteristics such as dynamic and static behaviors of these starters also vary significantly, depending on the type of starter and the size or configuration (single or multiple shafts) of the engine to be started. This paper provides an overall comparative background of the commonly available gas turbine engine starters. It also presents numerical results comparing hot start characteristics of single, two, and three shaft engines with cold and hot ends. The possibility of a safe engine hot starting is a valid asset in some service areas, mainly military applications. The comparisons include starter power and gas producer speed (NGP) as the function of engine acceleration, and also starter torque as a function of the % NGP. Fuel consumption of the engine during the hot start is simulated and presented as a function of the load. The impact of an engine configuration on engine starting characteristics is implicated.

scholarly journals The INVESTIGATION OF THE DYNAMIC CHARACTERISTICS OF TURBINE IMPELLER DISC OF GAS TURBINE ENGINE USING ANSYS SOFTWARE

2021 ◽  
Vol 3 (SI3) ◽  
pp. first
Author(s):  
THANH NGOC HUYNH ◽  
TOẢN QUỐC TRẦN ◽  
QUYẾT THÀNH PHẠM
Keyword(s):  
Gas Turbine ◽  
Dynamic Properties ◽  
Gas Turbine Engine ◽  
Simulation Software ◽  
Advanced Technology ◽  
Ansys Software ◽  
Engine Operation ◽  
Turbine Engine ◽  
The Impact ◽  
Turbine Impeller

The rotating blades of a compressor or turbine in a gas turbine engine are made up of blades installed on the impeller disc. In particular, the impeller disc needs to be designed, manufactured, and installed to ensure its reliability and safety regarding the strict standards. If damage occurs during the operating process of the impeller disc, it will not only damage the motor but also endanger operators and other equipment. To increase the service time of the engine as well as shorten the production cost, gas turbine manufacturers around the globe are constantly improving technology. In which the monolithic casting impeller is an advanced technology that helps bring down the impeller mass, increasing its life by reducing the shock force on the connection the blades to the rotating disc. Nevertheless, this type of monolithic casting impeller disc reduces its damping effectiveness, which causes the oscillation force to increase significantly. In order to resolve this problem, it is necessary to look into these factors affecting the oscillation of the impeller disc. This paper presents the factors that affect the oscillation of the impeller disc through the study of the dynamic properties of its constituent components. The specific oscillation of the impeller disc, its own oscillation, as well as the impact of factors occurring during the operating of the disc was calculated by using ANSYS simulation software. By creating a three-dimensional model of the turbine blades in gas turbine engine ДP76, the individual oscillation values in a variety of engine operation modes were calculated to compare with the actual value while the engine is operating. The results have good agreement with the measured values. This affirms the advantages and prospects in applying ANSYS software to the design and manufacture of the turbine impeller disc.

Impact of Manufacturing Variability on Combustor Liner Durability

2006 ◽  
Author(s):  
Sean D. Bradshaw ◽  
Ian A. Waitz
Keyword(s):  
Wall Temperature ◽  
Low Cycle Fatigue ◽  
Outlet Temperature ◽  
Gas Temperature ◽  
Commercial Aircraft ◽  
Temperature Variations ◽  
Turbine Engine ◽  
Deterministic Methods ◽  
The Impact ◽  
Combustor Liner

This paper presents a probabilistic model that quantifies the impact of manufacturing variability on combustor liner temperature and low cycle fatigue life. This model is applied to a gas turbine engine combustor for a commercial aircraft and assessed using combustor liner wall temperature and outlet gas temperature measurements. A probabilistic analysis shows that the model estimates cup-to-cup outlet temperature variations and liner wall temperature variations consistent with these measurements. Furthermore, this analysis shows that the typical liner life is 25 percent less than the life estimated using deterministic methods. In addition, approximately 99 percent of the combustors designed using deterministic methods will fail earlier than predicted. A sensitivity analysis shows that the variability in combustor unmixedness is the key driver of liner life.

scholarly journals Operation Evaluation Method for Marine Turbine Combustion Engines in Terms of Energetics

2016 ◽  
Vol 23 (4) ◽  
pp. 67-72
Author(s):  
Marek Dzida ◽  
Jerzy Girtler
Keyword(s):  
Energy Conversion ◽  
Internal Energy ◽  
Internal Combustion Engines ◽  
Combustion Engine ◽  
Internal Combustion ◽  
Combustion Engines ◽  
Combustion Chambers ◽  
Engine Operation ◽  
Turbine Engine ◽  
The Impact

Abstract An evaluation proposal (quantitative determination) of any combustion turbine engine operation has been presented, wherein the impact energy occurs at a given time due to Energy conversion. The fact has been taken into account that in this type of internal combustion engines the energy conversion occurs first in the combustion chambers and in the spaces between the blade of the turbine engine. It was assumed that in the combustion chambers occurs a conversion of chemical energy contained in the fuel-air mixture to the internal energy of the produced exhaust gases. This form of energy conversion has been called heat. It was also assumed that in the spaces between the blades of the rotor turbine, a replacement occurs of part of the internal energy of the exhaust gas, which is their thermal energy into kinetic energy conversion of its rotation. This form of energy conversion has been called the work. Operation of the combustion engine has been thus interpreted as a transmission of power receivers in a predetermined time when there the processing and transfer in the form (means) of work and heat occurs. Valuing the operation of this type of internal combustion engines, proposed by the authors of this article, is to determine their operation using physical size, which has a numerical value and a unit of measurement called joule-second [joule x second]. Operation of the combustion turbine engine resulting in the performance of the turbine rotor work has been presented, taking into account the fact that the impeller shaft is connected to the receiver, which may be a generator (in the case of one-shaft engine) or a propeller of the ship (in the case of two or three shaft engine).

The efficiency of application of virtual cross-sections method and hypotheses MELS in problems of wave signal propagation in elastic waveguides with rough surfaces

2016 ◽  
pp. 3564-3575 ◽  
Author(s):  
Ara Sergey Avetisyan
Keyword(s):  
Half Space ◽  
Cross Sections ◽  
Classical Method ◽  
Signal Propagation ◽  
Elastic Half Space ◽  
Layered Systems ◽  
Surface Layers ◽  
Inhomogeneous Surface ◽  
Wave Signal ◽  
The Impact

The efficiency of virtual cross sections method and MELS (Magneto Elastic Layered Systems) hypotheses application is shown on model problem about distribution of wave field in thin surface layers of waveguide when plane wave signal is propagating in it. The impact of surface non-smoothness on characteristics of propagation of high-frequency horizontally polarized wave signal in isotropic elastic half-space is studied. It is shown that the non-smoothness leads to strong distortion of the wave signal over the waveguide thickness and along wave signal propagation direction as well.  Numerical comparative analysis of change in amplitude and phase characteristics of obtained wave fields against roughness of weakly inhomogeneous surface of homogeneous elastic half-space surface is done by classical method and by proposed approach for different kind of non-smoothness.

scholarly journals A note on the relations between elastic and inelastic interactions and increasing ratio σel(s)/σtot(s) at the LHC

2019 ◽  
Vol 34 (32) ◽  
pp. 1950259 ◽  
Author(s):  
S. M. Troshin ◽  
N. E. Tyurin
Keyword(s):  
Elastic Scattering ◽  
Energy Dependence ◽  
Impact Parameter ◽  
Cross Sections ◽  
Parameter Dependence ◽  
Slope Parameter ◽  
Short Notice ◽  
Inelastic Interactions ◽  
The Impact ◽  
Mode A

We comment briefly on relations between the elastic and inelastic cross-sections valid for the shadow and reflective modes of the elastic scattering. Those are based on the unitarity arguments. It is shown that the redistribution of the probabilities of the elastic and inelastic interactions (the form of the inelastic overlap function becomes peripheral) under the reflective scattering mode can lead to increasing ratio of [Formula: see text] at the LHC energies. In the shadow scattering mode, the mechanism of this increase is a different one, since the impact parameter dependence of the inelastic interactions probability is central in this mode. A short notice is also given on the slope parameter and the leading contributions to its energy dependence in both modes.

scholarly journals Charged current Drell-Yan production at N3LO

2020 ◽  
Vol 2020 (11) ◽  
Author(s):  
Claude Duhr ◽  
Falko Dulat ◽  
Bernhard Mistlberger
Keyword(s):  
Cross Section ◽  
Cross Sections ◽  
Production Cross Section ◽  
Production Cross ◽  
Hadron Collider ◽  
Charge Asymmetry ◽  
Charged Current ◽  
Leading Order ◽  
Neutrino Pair ◽  
The Impact

Abstract We present the production cross section for a lepton-neutrino pair at the Large Hadron Collider computed at next-to-next-to-next-to-leading order (N3LO) in QCD perturbation theory. We compute the partonic coefficient functions of a virtual W± boson at this order. We then use these analytic functions to study the progression of the perturbative series in different observables. In particular, we investigate the impact of the newly obtained corrections on the inclusive production cross section of W± bosons, as well as on the ratios of the production cross sections for W+, W− and/or a virtual photon. Finally, we present N3LO predictions for the charge asymmetry at the LHC.

scholarly journals A New Method to Determine the Impact of Individual Field Quantities on Cycle-to-Cycle Variations in a Spark-Ignited Gas Engine

Energies ◽  
2021 ◽  
Vol 14 (14) ◽  
pp. 4136
Author(s):  
Clemens Gößnitzer ◽  
Shawn Givler
Keyword(s):  
Kinetic Energy ◽  
Flow Field ◽  
Turbulent Kinetic Energy ◽  
Negative Impact ◽  
Operating Conditions ◽  
Engine Operation ◽  
Gas Engine ◽  
Cycle Simulation ◽  
Simulation Results ◽  
The Impact

Cycle-to-cycle variations (CCV) in spark-ignited (SI) engines impose performance limitations and in the extreme limit can lead to very strong, potentially damaging cycles. Thus, CCV force sub-optimal engine operating conditions. A deeper understanding of CCV is key to enabling control strategies, improving engine design and reducing the negative impact of CCV on engine operation. This paper presents a new simulation strategy which allows investigation of the impact of individual physical quantities (e.g., flow field or turbulence quantities) on CCV separately. As a first step, multi-cycle unsteady Reynolds-averaged Navier–Stokes (uRANS) computational fluid dynamics (CFD) simulations of a spark-ignited natural gas engine are performed. For each cycle, simulation results just prior to each spark timing are taken. Next, simulation results from different cycles are combined: one quantity, e.g., the flow field, is extracted from a snapshot of one given cycle, and all other quantities are taken from a snapshot from a different cycle. Such a combination yields a new snapshot. With the combined snapshot, the simulation is continued until the end of combustion. The results obtained with combined snapshots show that the velocity field seems to have the highest impact on CCV. Turbulence intensity, quantified by the turbulent kinetic energy and turbulent kinetic energy dissipation rate, has a similar value for all snapshots. Thus, their impact on CCV is small compared to the flow field. This novel methodology is very flexible and allows investigation of the sources of CCV which have been difficult to investigate in the past.

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