Rotordynamic Analysis of a 5-Kilonewton Thrust Gas Turbine by Considering Bearing Dynamics

Creci, Geraldo; Menezes, João Carlos; Barbosa, João Roberto; Corra, Joao Aparecido

doi:10.2514/1.b34104

Cited by 15 publications

(3 citation statements)

References 7 publications

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“…The generated mesh should be able to provide sufficiently accurate results according to the complexity of the geometry and physical phenomena involved. Several complex applications can be analyzed with sufficient accuracy level [4,5]. In computational numerical simulations, the pre-processing phase is one of the "bottle-neck" with respect to the computer processing time.…”

Section: Introductionmentioning

confidence: 99%

A Simplified Mesh Generation Scheme for 3D Geometries Composed by Planar Faces to be used with BEM

Rodrigues¹

2021

IJAERS

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This paper presents the development of a simplified mesh generation scheme for three-dimensional boundary element method (BEM). The developed program presented in this work takes into account three-dimensional geometries composed by planar faces. This is a simplification regarding the form of the acceptable geometries, but a great variety of geometries and problems can be modelled with sufficient accuracy to perform numerical analysis. The main program's idea consists of moving each face belonging to the three-dimensional geometry to bi-dimensional space using geometrical transformation matrices. In bidimensional space, then, it is applied a bi-dimensional mesh generation algorithm for element generation. After element generation is done, new geometrical transformations are applied in order to send the meshed face back to its original position in three-dimensional space. The continuity of the final mesh is assured by promoting the discretization of the edges of the geometry only once. The proposed scheme has several positive aspects regarding simplicity, efficiency and robustness. A practical and immediate use of the proposed algorithm can be found for those who already have a bi-dimensional mesh generator code implemented and intent to expand its functionalities to treat simple three-dimensional geometries composed by planar faces. Several examples of meshes in arbitrary three-dimensional geometries composed by planar faces are presented in order to illustrate the capabilities of the developed computational program and some computational simulations have been performed to show the quality of the meshes in problems with specific boundary conditions.

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Section: Introductionmentioning

confidence: 99%

A Simplified Mesh Generation Scheme for 3D Geometries Composed by Planar Faces to be used with BEM

Rodrigues¹

2021

IJAERS

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“…The aeronautical gas turbine studied in this work has been developed at the Instituto Tecnológico de Aeronáutica in partnership with TGM Turbinas Ltda and Departmento de Ciência e Tecnologia Aeroespacial, with financial support from FINEP/MCT. With an approximate weight of 650 N, a maximum diameter of 0.350 m, and a maximum length of 1.50 m, the aeronautical gas turbine is capable of generating 5 kN of thrust at the rotational speed of 28,150 rpm [2][3][4].…”

Section: Introductionmentioning

confidence: 99%

Finite Element Analysis to Verify the Structural Integrity of an Aeronautical Gas Turbine Disc Made from Inconel 713LC Superalloy

Leme

Creci

Jesus

et al. 2019

AEF

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Gas turbines are very important because they can be used in several areas, such as aeronautics and electric power generation systems. The operation of a gas turbine can be done by less pollutant fuels when compared to traditional kerosene, for example, resulting in less degradation to environment. Gas turbines may fail from a variety of sources, with the possibility of serious damage results. In this work, the structural integrity of the hot disc of an aeronautical gas turbine is addressed. Several numerical analyses have been performed by the finite element method: Temperature Distributions, Thermal Stresses and Dilatations, Structural Stresses and Deformations, Modal Behaviors and Fatigue Analysis. Creep of blades has also been considered. These are the most important failure modes that can happen to the studied hot disc under operating service. All these analysis have been performed considering the boundary conditions at the design point with maximum rotational speed. The mesh of the problem has been strictly evaluated by adaptive refinement of nodes and elements combined with a convergence analysis of results. Then, the material and basic properties of the hot disc have been defined to assure a normal operation free from failures. Therefore, the mechanical drawings of the studied hot turbine disc have been released for manufacturing and the construction of the first prototype of the aeronautical gas turbine is in testing phase showing that the results presented in this work are consistent.

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“…Visit to Propulsion Division of the IAE: The DCTA gas turbine project is housed in this institute. Some publications made by the Gas Turbine Group at ITA/IAE (DCTA) (Bringhenti and Barbosa, 2003, 2004c, 2004dBarbosa et al, 2011Barbosa et al, , 2012Tomita et al, 2005;Bringhenti et al, 2010;Silva, 2007;Silva et al, 2005;Creci Filho et al, 2009 indicate the capability of gas turbines' design and development. In this visit, the students are presented to test facilities, including one of the piston engines.…”

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confidence: 99%

Gas Turbine Course’s Teaching Process at Instituto Tecnológico de Aeronáutica: Theory and Laboratory

Bringhenti

Tomita²,

Barbosa³

2015

J.Aerosp. Technol. Manag.

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The Instituto Tecnológico de Aeronáutica (ITA) is an Engineering school maintained by the Air Force Command, Ministry of Defense. The aim of the Turbomachines Department at ITA is the human resources training for design and development of aeronautical and industrial gas turbines, necessary for the Gas Turbine Program of the Departamento de Ciência e Tecnologia Aeroespacial (DCTA). The human resources training is carried out in undergraduate and graduate courses at ITA, where topics in gas turbine and turbomachinery are taught. The gas turbine topic is taught in the undergraduate degree, in Mechanical-Aeronautical Engineering course, and focuses on gas turbines' performance for different configurations (turboshaft, turbojet and turbofan). Lecture notes containing the essential elements of the course are made available for the students, addressing the basic theory of the gas turbines required for the performance study at the design and off-design point. The technological aspects are presented and discussed during detailed studies of the actual cycle. Simple gas turbines and more sophisticated ones are studied, for both aeronautical and industrial application. Performance calculations at design and off-design point of the main engine's components and the cycle are done manually, encouraging students to develop spreadsheets. The theory is complemented with laboratory classes and technical visits, when the practicalities involving gas turbines operation and tests are presented to the students. As an activity laboratory class, the students perform disassembly-assembly of a small industrial gas turbine.

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Rotordynamic Analysis of a 5-Kilonewton Thrust Gas Turbine by Considering Bearing Dynamics

Cited by 15 publications

References 7 publications

A Simplified Mesh Generation Scheme for 3D Geometries Composed by Planar Faces to be used with BEM

A Simplified Mesh Generation Scheme for 3D Geometries Composed by Planar Faces to be used with BEM

Finite Element Analysis to Verify the Structural Integrity of an Aeronautical Gas Turbine Disc Made from Inconel 713LC Superalloy

Gas Turbine Course’s Teaching Process at Instituto Tecnológico de Aeronáutica: Theory and Laboratory

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