ATEC: The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations: Part 2 — Numerical Simulations

Garrard, Doug

doi:10.1115/96-gt-194

Cited by 10 publications

(4 citation statements)

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“…As far as solution of non-linear partial differential equation (PDEs) and ordinary differential equations (ODEs) involved in the physical models are concerned, a proper numerical technique is required to convert them into a linearized equation for simulation purposes. Various numerical methodologies such as the Newton–Raphson Method [ 7 , 10 , 12 , 45 , 71 , 73 , 110 ], Runge–Kutta method [ 66 , 73 , 74 , 118 ], Taylor series [ 119 ], Euler implicit and explicit numerical solution method [ 118 , 120 ], finite difference method (FDM) [ 52 , 66 , 110 , 121 ], linear interpolation method [ 74 ], and trapezoidal rule [ 66 , 122 ] have been purposed and utilized by the researchers. However, each method has its own benefits and limitation depending upon the complexity of the mathematical equations involved in transient models.…”

Section: Methods and Techniques For Transient Modelsmentioning

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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Section: Methods and Techniques For Transient Modelsmentioning

confidence: 99%

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

Hashmi

Lemma

Ahsan

et al. 2021

Entropy

View full text Add to dashboard Cite

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“…This level of modeling fidelity for the key engine components of the propulsion system will allow for accurate representation of the thrust dynamics. Integrated propulsion system one-dimensional dynamic models have been developed in support of previous NASA supersonic projects by Garrard, [14][15][16] Gamble, 17 Numbers, 18 and Giannola. 19 The distinction in the work presented here is that the main goal is to provide a platform for integration into a high fidelity ASE vehicle model.…”

Section: B Propulsion System Modelmentioning

confidence: 99%

Towards an Aero-Propulso-Servo-Elasticity Analysis of a Commercial Supersonic Transport

Connolly

Chwalowski

Sanetrik

et al. 2016

15th Dynamics Specialists Conference

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This paper covers the development of an aero-propulso-servo-elastic (APSE) model using computational fluid dynamics (CFD) and linear structural deformations. The APSE model provides the integration of the following two previously developed nonlinear dynamic simulations: a variable cycle turbofan engine and an elastic supersonic commercial transport vehicle. The primary focus of this study is to provide a means to include relevant dynamics of a turbomachinery propulsion system into the aeroelastic studies conducted during a vehicle design, which have historically neglected propulsion effects. A high fidelity CFD tool is used here for the integration platform. The elastic vehicle neglecting the propulsion system serves as a comparison of traditional approaches to the APSE results. An overview of the methodology is presented for integrating the propulsion system and elastic vehicle. Static aeroelastic analysis comparisons between the traditional and developed APSE models for a wing tip deflection indicate that the propulsion system impact on the vehicle elastic response could increase the deflection by approximately ten percent.

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“…or one-dimensional [2,3], are often based upon single-stage or full characteristic maps of the turbomachine. These maps are often inaccurate or simply not available, and their use is not compatible with the exploratory aspect of the simulation [2].…”

Section: Introductionmentioning

confidence: 99%

A quasi-one-dimensional CFD model for multistage turbomachines

Léonard

Adam

2008

J. Therm. Sci.

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The objective of this paper is to present a fast and reliable CFD model that is able to simulate stationary and transient operations of multistage compressors and turbines. This analysis tool is based on an adapted version of the Euler equations solved by a time-marching, finite-volume method. The Euler equations have been extended by including source terms expressing the blade-flow interactions. These source terms are determined using the velocity triangles and a row-by-row representation of the blading at mid-span. The losses and deviations undergone by the fluid across each blade row are supplied by correlations. The resulting flow solver is a performance prediction tool based only on the machine geometry, offering the possibility of exploring the entire characteristic map of a multistage compressor or turbine. Its efficiency in terms of CPU time makes it possible to couple it to an optimization algorithm or to a gas turbine performance tool. Different test-cases are presented for which the calculated characteristic maps are compared to experimental ones.

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ATEC: The Aerodynamic Turbine Engine Code for the Analysis of Transient and Dynamic Gas Turbine Engine System Operations: Part 2 — Numerical Simulations

Cited by 10 publications

References 0 publications

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

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

Towards an Aero-Propulso-Servo-Elasticity Analysis of a Commercial Supersonic Transport

A quasi-one-dimensional CFD model for multistage turbomachines

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