Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace

Sheng, Hanlin; Zhang, Tianhong; Jiang, Wei

doi:10.1515/tjj-2015-0033

Cited by 7 publications

(6 citation statements)

References 4 publications

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“…Figure 20 shows THD (Total Harmonic Distortion), a measurement of the harmonic distortion present in a signal and is defined as the ratio of the sum of the powers of all harmonic components to the power of the fundamental frequency, of extracted current from the network. THD value is obtained as: (15) where I 1 is the main component of current and I k is the kth harmonic component of current. In this section, based on the speed reference curve, the set of network-drive-starter motor-gas turbine is simulated.…”

Section: Analysis Of Simulation Resultsmentioning

confidence: 99%

“…A case study focusing on the effects of ground starts was added that compared findings from engine dry crank with those of simulations, corroborating the ability of simulation for estimation of proper trends. Sheng et al [15] employed an inexact computational approach regarding low-speed part behavior in aeroengines so as to obtain comprehensive component characteristics with the aid of integrating empirical data above idle. The result was a turboshaft engine model that could consider the start-up state.…”

Section: Introductionmentioning

confidence: 99%

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Modeling and Control of the Starter Motor and Start-Up Phase for Gas Turbines

2019

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Improving the performance of industrial gas turbines has always been at the focus of attention of researchers and manufacturers. Nowadays, the operating environment of gas turbines has been transformed significantly respect to the very fast growth of renewable electricity generation where gas turbines should provide a safe, reliable, fast, and flexible transient operation to support their renewable partners. So, having a reliable tools to predict the transient behavior of the gas turbine is becoming more and more important. Regarding the response time and flexibility, improving the turbine performance during the start-up phase is an important issue that should be taken into account by the turbine manufacturers. To analyze the turbine performance during the start-up phase and to implement novel ideas so as to improve its performance, modeling, and simulation of an industrial gas turbine during cold start-up phase is investigated this article using an integrated modular approach. During this phase, a complex mechatronic system comprised of an asynchronous AC motor (electric starter), static frequency converter drive, and gas turbine exists. The start-up phase happens in this manner: first, the clutch transfers the torque generated by the electric starter to the gas turbine so that the turbine reaches a specific speed (cranking stage). Next, the turbine spends some time at this speed (purging stage), after which the turbine speed decreases, sparking stage begins, and the turbine enters the warm start-up phase. It is, however, possible that the start-up process fails at an intermediate stage. Such unsuccessful start-ups can be caused by turbine vibrations, the increase in the gradients of exhaust gases, or issues with fuel spray nozzles. If, for any reason, the turbine cannot reach the self-sustained speed and the speed falls below a certain threshold, the clutch engages once again with the turbine shaft and the start-up process is repeated. Consequently, when modeling the start-up phase, we face discontinuities in performance and a system with variable structure owing to the existence of clutch. Modeling the start-up phase, which happens to exist in many different fields including electric and mechanical application, brings about problems in numerical solutions (such as algebraic loop). Accordingly, this study attempts to benefit from the bond graph approach (as a powerful physical modeling approach) to model such a mechatronic system. The results confirm the effectiveness of the proposed approach in detailed performance prediction of the gas turbine in start-up phase.

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Section: Analysis Of Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Modeling and Control of the Starter Motor and Start-Up Phase for Gas Turbines

2019

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“…Hence, an engine comprising of higher starter capacity is very beneficial in terms of fuel saving and preventing the hot parts of the engine from damage due to excessive fuel flow. Additionally, some other researchers have developed transient models for idle and sub-idle regimes for civil aero engines, such as sheng et al [ 87 ], who suggested a stage stacking method for extrapolation of low speed region in order to simulate a full rage startup transient model for a turboshaft engine. Similarly, Kim et al [ 88 ] have used a thermodynamic model for a triple-shaft turbofan engine in order to simulate three different kind of startup regimes, i.e., wind milling, sub-idle and idle to maximum power ranges.…”

Section: Classifications Of Transient Regimes In Igtmentioning

confidence: 99%

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Hashmi

Lemma

Ahsan

et al. 2021

Entropy

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Generally, industrial gas turbines (IGT) face transient behavior during start-up, load change, shutdown and variations in ambient conditions. These transient conditions shift engine thermal equilibrium from one steady state to another steady state. In turn, various aero-thermal and mechanical stresses are developed that are adverse for engine’s reliability, availability, and overall health. The transient behavior needs to be accurately predicted since it is highly related to low cycle fatigue and early failures, especially in the hot regions of the gas turbine. In the present paper, several critical aspects related to transient behavior and its modeling are reviewed and studied from the point of view of identifying potential research gaps within the context of fault detection and diagnostics (FDD) under dynamic conditions. Among the considered topics are, (i) general transient regimes and pertinent model formulation techniques, (ii) control mechanism for part-load operation, (iii) developing a database of variable geometry inlet guide vanes (VIGVs) and variable bleed valves (VBVs) schedules along with selection framework, and (iv) data compilation of shaft’s polar moment of inertia for different types of engine’s configurations. This comprehensive literature document, considering all the aspects of transient behavior and its associated modeling techniques will serve as an anchor point for the future researchers, gas turbine operators and design engineers for effective prognostics, FDD and predictive condition monitoring for variable geometry IGT.

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“…The following are mathematical models for each of them as well as atmospheric environment. 36 Atmospheric environment. The effects of atmospheric pressure and temperature on flight conditions are considered here.…”

Section: Mathematical Model For a Turboshaft Aeroenginementioning

confidence: 99%

Simulation and semi-physical verification of fuel metering unit model for turboshaft aeroengine

Wang

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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When modeling an aeroengine control system, effects of fuel metering unit are neglected or oversimplified, which most probably leads to unreliable simulation or experimental results. In order to well understand influences of fuel metering unit on performance of an aeroengine and to enrich the component-level model of a turboshaft aeroengine, a stepping motor controlled fuel metering unit is examined by combining process-based modeling and object-oriented modeling and is employed in the component-level engine model. Performances of the engine with and without the fuel metering unit are compared by simulation. The component-level engine model with the fuel metering unit characteristics considered meets the simulation requirements on the steady precision and can describe dynamics of the engine more precisely. A semi-physical experimental verification is implemented to confirm the influence of the fuel metering unit. The results show that simulation using the component-level engine model with the fuel metering unit sub-model is in accordance with the experiment, and that comparing to the engine model without fuel metering unit, the model with a fuel metering unit can extend the performance parameter response dozens of milliseconds.

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Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace

Cited by 7 publications

References 4 publications

Modeling and Control of the Starter Motor and Start-Up Phase for Gas Turbines

Modeling and Control of the Starter Motor and Start-Up Phase for Gas Turbines

Transient Behavior in Variable Geometry Industrial Gas Turbines: A Comprehensive Overview of Pertinent Modeling Techniques

Simulation and semi-physical verification of fuel metering unit model for turboshaft aeroengine

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