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Alain Batailly - One of the best experts on this subject based on the ideXlab platform.

  • Experimental and numerical simulation of a rotor/stator interaction event localized on a single blade within an industrial high-Pressure Compressor
    Journal of Sound and Vibration, 2016
    Co-Authors: Alain Batailly, Antoine Millecamps, Quentin Agrapart, Jeanfrancois Brunel
    Abstract:

    This contribution addresses a confrontation between the experimental simulation of a rotor/stator interaction case initiated by structural contacts with numerical predictions made with an in-house numerical strategy. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a short period of time. An in-depth analysis of experimental data first allows for a precise characterization of the interaction as a rubbing event involving the first torsional mode of a single blade. Numerical results are in good agreement with experimental observations: the critical angular speed, the wear patterns on the casing as well as the blade dynamics are accurately predicted. Through out the article, the in-house numerical strategy is also confronted to another numerical strategy that may be found in the literature for the simulation of rubbing events: key differences are underlined with respect to the prediction of non-linear interaction phenomena.

  • experimental and numerical simulation of a rotor stator interaction event localized on a single blade within an industrial high Pressure Compressor
    Journal of Sound and Vibration, 2016
    Co-Authors: Alain Batailly, Antoine Millecamps, Quentin Agrapart, Jeanfrancois Brunel
    Abstract:

    This contribution addresses a confrontation between the experimental simulation of a rotor/stator interaction case initiated by structural contacts with numerical predictions made with an in-house numerical strategy. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a short period of time. An in-depth analysis of experimental data first allows for a precise characterization of the interaction as a rubbing event involving the first torsional mode of a single blade. Numerical results are in good agreement with experimental observations: the critical angular speed, the wear patterns on the casing as well as the blade dynamics are accurately predicted. Through out the article, the in-house numerical strategy is also confronted to another numerical strategy that may be found in the literature for the simulation of rubbing events: key differences are underlined with respect to the prediction of non-linear interaction phenomena.

  • Experimental and numerical simulation of a contact induced rotor/stator interaction inside an aircraft engine high-Pressure Compressor
    2016
    Co-Authors: Alain Batailly, Quentin Agrapart, Antoine Millecamps
    Abstract:

    The development of a predictive numerical strategy for the simulation of rotor/stator interactions is a concern for several aircraft engine manufacturers. As a matter of fact, modern designs of aircraft engines feature reduced operating clearances between rotating and static components which yields more frequent structural contacts. Subsequent interaction phenomena (be it rubbing events, modal interaction or whirl motions) are not yet fully understood. For that reason, experimental data obtained from set-ups dedicated to the simulation of such interactions are scrutinized and are key in: (1) increasing the knowledge of the interaction phenomena and (2) allowing for a calibration of the numerical models with realistic events. In this contribution, the focus is made on an experimental set-up in Snecma facilities. It features a full-scale high-Pressure Compressor stage and aims at simulating contact induced interactions between one of the blades (slightly longer than the other ones) and the surrounding abradable coating that is deposited along the casing circumference. For this experimental set-up, it is found that the witnessed interaction involves a single blade---thus it should be analyzed as a sequence of rubbing events---and more specifically its first torsional mode, which is its second free-vibration mode. The focus is made both on the presentation of the experimental set-up and on the confrontation with the numerical results. Numerical results are analyzed by means of adaptative signal processing techniques and the consistency between numerical results and experimental observations is underlined both in time and frequency domains. In particular, the numerical strategy developed for Snecma is shown to predict very accurately the nature of the interaction as wear patterns obtained experimentally and numerically are a match. This numerical/experimental confrontation is the first attempt to calibrate a sophisticated numerical strategy with experimental data acquired within the high-Pressure Compressor of an aircraft engine for the simulation of rotor/stator interactions. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a very short period of time. The ability of the numerical strategy to predict torsion induced interactions opens avenues for further analyses in turbine stages and with more sophisticated models including mistuned bladed disks and multi-stage components.

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.Copyright © 2014 by ASME

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincaré maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.

Francois Maurice Garcin - One of the best experts on this subject based on the ideXlab platform.

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.Copyright © 2014 by ASME

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincaré maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    Volume 7B: Structures and Dynamics, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincare maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.Copyright © 2014 by ASME

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.

Antoine Millecamps - One of the best experts on this subject based on the ideXlab platform.

  • Experimental and numerical simulation of a rotor/stator interaction event localized on a single blade within an industrial high-Pressure Compressor
    Journal of Sound and Vibration, 2016
    Co-Authors: Alain Batailly, Antoine Millecamps, Quentin Agrapart, Jeanfrancois Brunel
    Abstract:

    This contribution addresses a confrontation between the experimental simulation of a rotor/stator interaction case initiated by structural contacts with numerical predictions made with an in-house numerical strategy. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a short period of time. An in-depth analysis of experimental data first allows for a precise characterization of the interaction as a rubbing event involving the first torsional mode of a single blade. Numerical results are in good agreement with experimental observations: the critical angular speed, the wear patterns on the casing as well as the blade dynamics are accurately predicted. Through out the article, the in-house numerical strategy is also confronted to another numerical strategy that may be found in the literature for the simulation of rubbing events: key differences are underlined with respect to the prediction of non-linear interaction phenomena.

  • experimental and numerical simulation of a rotor stator interaction event localized on a single blade within an industrial high Pressure Compressor
    Journal of Sound and Vibration, 2016
    Co-Authors: Alain Batailly, Antoine Millecamps, Quentin Agrapart, Jeanfrancois Brunel
    Abstract:

    This contribution addresses a confrontation between the experimental simulation of a rotor/stator interaction case initiated by structural contacts with numerical predictions made with an in-house numerical strategy. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a short period of time. An in-depth analysis of experimental data first allows for a precise characterization of the interaction as a rubbing event involving the first torsional mode of a single blade. Numerical results are in good agreement with experimental observations: the critical angular speed, the wear patterns on the casing as well as the blade dynamics are accurately predicted. Through out the article, the in-house numerical strategy is also confronted to another numerical strategy that may be found in the literature for the simulation of rubbing events: key differences are underlined with respect to the prediction of non-linear interaction phenomena.

  • Experimental and numerical simulation of a contact induced rotor/stator interaction inside an aircraft engine high-Pressure Compressor
    2016
    Co-Authors: Alain Batailly, Quentin Agrapart, Antoine Millecamps
    Abstract:

    The development of a predictive numerical strategy for the simulation of rotor/stator interactions is a concern for several aircraft engine manufacturers. As a matter of fact, modern designs of aircraft engines feature reduced operating clearances between rotating and static components which yields more frequent structural contacts. Subsequent interaction phenomena (be it rubbing events, modal interaction or whirl motions) are not yet fully understood. For that reason, experimental data obtained from set-ups dedicated to the simulation of such interactions are scrutinized and are key in: (1) increasing the knowledge of the interaction phenomena and (2) allowing for a calibration of the numerical models with realistic events. In this contribution, the focus is made on an experimental set-up in Snecma facilities. It features a full-scale high-Pressure Compressor stage and aims at simulating contact induced interactions between one of the blades (slightly longer than the other ones) and the surrounding abradable coating that is deposited along the casing circumference. For this experimental set-up, it is found that the witnessed interaction involves a single blade---thus it should be analyzed as a sequence of rubbing events---and more specifically its first torsional mode, which is its second free-vibration mode. The focus is made both on the presentation of the experimental set-up and on the confrontation with the numerical results. Numerical results are analyzed by means of adaptative signal processing techniques and the consistency between numerical results and experimental observations is underlined both in time and frequency domains. In particular, the numerical strategy developed for Snecma is shown to predict very accurately the nature of the interaction as wear patterns obtained experimentally and numerically are a match. This numerical/experimental confrontation is the first attempt to calibrate a sophisticated numerical strategy with experimental data acquired within the high-Pressure Compressor of an aircraft engine for the simulation of rotor/stator interactions. Contrary to previous studies carried out within the low-Pressure Compressor of an aircraft engine, this interaction is found to be non-divergent: high amplitudes of vibration are experimentally observed and numerically predicted over a very short period of time. The ability of the numerical strategy to predict torsion induced interactions opens avenues for further analyses in turbine stages and with more sophisticated models including mistuned bladed disks and multi-stage components.

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.Copyright © 2014 by ASME

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincaré maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.

Mathias Legrand - One of the best experts on this subject based on the ideXlab platform.

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power-transactions of The Asme, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.Copyright © 2014 by ASME

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincaré maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.

  • High-Pressure Compressor blade dynamics under aerodynamic and blade-tip unilateral contact forcings
    Volume 7B: Structures and Dynamics, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Francois Maurice Garcin
    Abstract:

    Recent studies focused on the numerical prediction of structural instabilities that may arise in rotating components of an aircraft engine. These instabilities are commonly classified into two categories: those induced by aerodynamic phenomena (such as the Pressure applied on the blade by the incoming air flow) and those related to structural phenomena (such as potential blade/casing contacts). Based on an existing numerical strategy for the analysis of rotor/stator interactions induced by unilateral contacts between rotating and static components, this paper aims at combining both types of instabilities and provides a qualitative analysis of structural interactions that may arise within the high-Pressure Compressor of an aircraft engine. The aerodynamic Pressure on the blade is simplified as a sinusoidal external load whose frequency depends on the number of upstream guide vanes. Results are presented both in time and frequency domains. Detailed bifurcation diagrams and Poincare maps underline the fundamental differences in the nature of the witnessed interactions with and without aerodynamic loading on the blade.Copyright © 2014 by ASME

  • Redesign of a High-Pressure Compressor Blade Accounting for Nonlinear Structural Interactions
    Journal of Engineering for Gas Turbines and Power, 2014
    Co-Authors: Alain Batailly, Mathias Legrand, Antoine Millecamps, Sébastien Cochon, Francois Maurice Garcin
    Abstract:

    Recent numerical developments dedicated to the simulation of rotor/stator interaction involving direct structural contacts have been integrated within the Snecma industrial environment. This paper presents the first attempt to benefit from these developments and account for structural blade/casing contacts at the design stage of a high-Pressure Compressor blade. The blade of interest underwent structural divergence after blade/abradable coating contact occurrences on a rig test. The design improvements were carried out in several steps with significant modifications of the blade stacking law while maintaining aerodynamic performance of the original blade design. After a brief presentation of the proposed design strategy, basic concepts associated with the design variations are recalled. The iterated profiles are then numerically investigated and compared with respect to key structural criteria such as: (1) their mass, (2) the residual stresses stemming from centrifugal stiffening, (3) the vibratory level under aerodynamic forced response and (4) the vibratory levels when unilateral contact occurs. Significant improvements of the final blade design are found: the need for an early integration of nonlinear structural interactions criteria in the design stage of modern aircraft engines components is highlighted.

J. Hourmouziadis - One of the best experts on this subject based on the ideXlab platform.

  • Non-Engine Order Blade Vibration in a High Pressure Compressor
    Proceedings of the 12th International Symposium on Airbreathing Engines, 1995
    Co-Authors: M Baumgartner, F Kameier, J. Hourmouziadis
    Abstract:

    High amplitude levels of blade vibration have occurred on the first rotor of a multi stage high Pressure Compressor. The frequencies are not in resonance with harmonics of the rotor speed. The excitation is aerodynamically caused and associated with a rotating flow instability in the blade tip region of the first Compressor stage. A vortex shedding mechanism can be interpreted as a rotating source to generate Pressure waves. The source moves relative to the blade row at a fraction of the rotor speed, similar to the ’well known mechanism’ of rotating stall. To investigate the unsteady flow field in the tip region of the rotor and its relation to the blade vibration, measurements of the Pressure and velocity fluctuations in the vicinity of the blade tips are compared with blade vibrations. A calculation model of the spectral characteristics of the Pressure fluctuations confirms the measured data. The effect is sensitive to aerodynamic blade loading so that a modification in the design could reduce the mechanism of the rotating excitation.