Q3141364 (Q3141364): Difference between revisions
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(Created claim: summary (P836): FOR EFFICIENCY REASONS, AXIAL COMPRESSORS OF AERONAUTICAL ENGINES TYPICALLY OPERATE AT HIGH COMPRESSION RATIOS. HOWEVER, FROM A CERTAIN THRESHOLD, THESE DEVICES PRESENT NUMEROUS INSTABILITY, SUCH AS THE SO-CALLED “SURGE” AND “ROTATING STALL”, WHICH COMPROMISE THEIR MECHANICAL INTEGRITY. CURRENTLY, THE DESCRIPTION OF THE PHYSICAL PROCESSES THAT PRODUCE THESE INSTABILITY IS STILL INCOMPLETE, ESPECIALLY IN THE CASE OF HIGH-SPEED COMPRESSORS. FOR EX...) |
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FOR EFFICIENCY REASONS, AXIAL COMPRESSORS OF AERONAUTICAL ENGINES TYPICALLY OPERATE AT HIGH COMPRESSION RATIOS. HOWEVER, FROM A CERTAIN THRESHOLD, THESE DEVICES PRESENT NUMEROUS INSTABILITY, SUCH AS THE SO-CALLED “SURGE” AND “ROTATING STALL”, WHICH COMPROMISE THEIR MECHANICAL INTEGRITY. CURRENTLY, THE DESCRIPTION OF THE PHYSICAL PROCESSES THAT PRODUCE THESE INSTABILITY IS STILL INCOMPLETE, ESPECIALLY IN THE CASE OF HIGH-SPEED COMPRESSORS. FOR EXAMPLE, THE CONNECTION BETWEEN THE VARIOUS MECHANISMS OF INSTABILITY IS PARTIALLY UNKNOWN AS IS THE INFLUENCE THAT THE COMPRESSOR GEOMETRIA HAS ON THE APPEARANCE OF THESE INSTABILITY (GUIDE WINGS, PROFILE OF THE BLADES, ROTOR GAME, CARTER AND ROTOR-STATOR INTERACTION). Better COMPRETION OF THESE ASPECTS IS NEED TO IMPROVE THE EFFECTION OF THESE DISPOSITIVES WITHOUT PROVIDED THE APARICTION OF INESTABILITIES._x000D_ _x000D_ The present PROJECT OF PROJECT FOR FUNDAMENTAL ASPECTS OF THE PHISIC MECHANISMES INFORMATION instability IN Axial COMPRESSOURS AS YOUR CONTROL MEDIANT TECHNICAL AND RECIENT TECHNICAL AND RECIENTS FOR THE STUDY OF STABILITY AND SENSIBILITY ASSISTANCE AS NUMMERICAL OPTIMISATION._x000D_ _x000D_ PERSIGUED TWO OBJECTIVES IN THIS PROJECT. THE FIRST IS TO DEVELOP AND VALIDATE EFFICIENT COMPUTATIONAL TOOLS FOR CONDUCTING STABILITY AND GLOBAL SENSITIVITY STUDIES AS WELL AS THE AERODYNAMIC OPTIMISATION OF NON-STATIONARY FLOWS IN TURBOMAQUINAS. THE SECOND OBJECTIVE IS TO IMPROVE THE CURRENT KNOWLEDGE OF INSTABILITY IN COMPRESSORS AND THEIR CONTROL BY CONSIDERING FOR THIS PURPOSE A HIERARCHY OF PHYSICAL MODELS OF INCREASING COMPLEXITY THAT PRESENT THIS TYPE OF INSTABILITY: A ROTOR CASCADE AS WELL AS A ROTOR-STATOR STAGE CONSISTING OF AN ARBITRARY NUMBER OF BLADES, INCLUDING REALISTIC MODELS FOR ADMISSION AND DISCHARGE. USING NUMERIC CODES SPECIFICALLY DESIGNED FOR THIS TASK, WE WILL FOCUS ON THE DETAILS OF THE PHYSICAL PHENOMENA THAT WILL TAKE PLACE AT THE LEVEL OF THE ALABE AS WELL AS THOSE RESULTING FROM INTERACTION WITH ADJACENT WINGS. THESE STUDIES ARE EXPECTED TO IMPROVE THE CURRENT KNOWLEDGE OF THESE INSTABILITYS AND THEIR SENSITIVITY TO CURRENT MANIPULATION, SUCH AS USING ACTUATORS OR CHANGES IN GEOMETRIA. THE INFORMATION OBTAINED IN THESE STUDIES WILL BE INCORPORATED IN PROBLEMS OF NUMERIC OPTIMISATION, BASED ON THE ASSISTANT OPERATOR, ORIENTED TO THE IMPROVEMENT OF THE STABILITY MARGIN IN AXIAL COMPRESSORS. (English) | |||||||||||||||
| Property / summary: FOR EFFICIENCY REASONS, AXIAL COMPRESSORS OF AERONAUTICAL ENGINES TYPICALLY OPERATE AT HIGH COMPRESSION RATIOS. HOWEVER, FROM A CERTAIN THRESHOLD, THESE DEVICES PRESENT NUMEROUS INSTABILITY, SUCH AS THE SO-CALLED “SURGE” AND “ROTATING STALL”, WHICH COMPROMISE THEIR MECHANICAL INTEGRITY. CURRENTLY, THE DESCRIPTION OF THE PHYSICAL PROCESSES THAT PRODUCE THESE INSTABILITY IS STILL INCOMPLETE, ESPECIALLY IN THE CASE OF HIGH-SPEED COMPRESSORS. FOR EXAMPLE, THE CONNECTION BETWEEN THE VARIOUS MECHANISMS OF INSTABILITY IS PARTIALLY UNKNOWN AS IS THE INFLUENCE THAT THE COMPRESSOR GEOMETRIA HAS ON THE APPEARANCE OF THESE INSTABILITY (GUIDE WINGS, PROFILE OF THE BLADES, ROTOR GAME, CARTER AND ROTOR-STATOR INTERACTION). Better COMPRETION OF THESE ASPECTS IS NEED TO IMPROVE THE EFFECTION OF THESE DISPOSITIVES WITHOUT PROVIDED THE APARICTION OF INESTABILITIES._x000D_ _x000D_ The present PROJECT OF PROJECT FOR FUNDAMENTAL ASPECTS OF THE PHISIC MECHANISMES INFORMATION instability IN Axial COMPRESSOURS AS YOUR CONTROL MEDIANT TECHNICAL AND RECIENT TECHNICAL AND RECIENTS FOR THE STUDY OF STABILITY AND SENSIBILITY ASSISTANCE AS NUMMERICAL OPTIMISATION._x000D_ _x000D_ PERSIGUED TWO OBJECTIVES IN THIS PROJECT. THE FIRST IS TO DEVELOP AND VALIDATE EFFICIENT COMPUTATIONAL TOOLS FOR CONDUCTING STABILITY AND GLOBAL SENSITIVITY STUDIES AS WELL AS THE AERODYNAMIC OPTIMISATION OF NON-STATIONARY FLOWS IN TURBOMAQUINAS. THE SECOND OBJECTIVE IS TO IMPROVE THE CURRENT KNOWLEDGE OF INSTABILITY IN COMPRESSORS AND THEIR CONTROL BY CONSIDERING FOR THIS PURPOSE A HIERARCHY OF PHYSICAL MODELS OF INCREASING COMPLEXITY THAT PRESENT THIS TYPE OF INSTABILITY: A ROTOR CASCADE AS WELL AS A ROTOR-STATOR STAGE CONSISTING OF AN ARBITRARY NUMBER OF BLADES, INCLUDING REALISTIC MODELS FOR ADMISSION AND DISCHARGE. USING NUMERIC CODES SPECIFICALLY DESIGNED FOR THIS TASK, WE WILL FOCUS ON THE DETAILS OF THE PHYSICAL PHENOMENA THAT WILL TAKE PLACE AT THE LEVEL OF THE ALABE AS WELL AS THOSE RESULTING FROM INTERACTION WITH ADJACENT WINGS. THESE STUDIES ARE EXPECTED TO IMPROVE THE CURRENT KNOWLEDGE OF THESE INSTABILITYS AND THEIR SENSITIVITY TO CURRENT MANIPULATION, SUCH AS USING ACTUATORS OR CHANGES IN GEOMETRIA. THE INFORMATION OBTAINED IN THESE STUDIES WILL BE INCORPORATED IN PROBLEMS OF NUMERIC OPTIMISATION, BASED ON THE ASSISTANT OPERATOR, ORIENTED TO THE IMPROVEMENT OF THE STABILITY MARGIN IN AXIAL COMPRESSORS. (English) / rank | |||||||||||||||
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| Property / summary: FOR EFFICIENCY REASONS, AXIAL COMPRESSORS OF AERONAUTICAL ENGINES TYPICALLY OPERATE AT HIGH COMPRESSION RATIOS. HOWEVER, FROM A CERTAIN THRESHOLD, THESE DEVICES PRESENT NUMEROUS INSTABILITY, SUCH AS THE SO-CALLED “SURGE” AND “ROTATING STALL”, WHICH COMPROMISE THEIR MECHANICAL INTEGRITY. CURRENTLY, THE DESCRIPTION OF THE PHYSICAL PROCESSES THAT PRODUCE THESE INSTABILITY IS STILL INCOMPLETE, ESPECIALLY IN THE CASE OF HIGH-SPEED COMPRESSORS. FOR EXAMPLE, THE CONNECTION BETWEEN THE VARIOUS MECHANISMS OF INSTABILITY IS PARTIALLY UNKNOWN AS IS THE INFLUENCE THAT THE COMPRESSOR GEOMETRIA HAS ON THE APPEARANCE OF THESE INSTABILITY (GUIDE WINGS, PROFILE OF THE BLADES, ROTOR GAME, CARTER AND ROTOR-STATOR INTERACTION). Better COMPRETION OF THESE ASPECTS IS NEED TO IMPROVE THE EFFECTION OF THESE DISPOSITIVES WITHOUT PROVIDED THE APARICTION OF INESTABILITIES._x000D_ _x000D_ The present PROJECT OF PROJECT FOR FUNDAMENTAL ASPECTS OF THE PHISIC MECHANISMES INFORMATION instability IN Axial COMPRESSOURS AS YOUR CONTROL MEDIANT TECHNICAL AND RECIENT TECHNICAL AND RECIENTS FOR THE STUDY OF STABILITY AND SENSIBILITY ASSISTANCE AS NUMMERICAL OPTIMISATION._x000D_ _x000D_ PERSIGUED TWO OBJECTIVES IN THIS PROJECT. THE FIRST IS TO DEVELOP AND VALIDATE EFFICIENT COMPUTATIONAL TOOLS FOR CONDUCTING STABILITY AND GLOBAL SENSITIVITY STUDIES AS WELL AS THE AERODYNAMIC OPTIMISATION OF NON-STATIONARY FLOWS IN TURBOMAQUINAS. THE SECOND OBJECTIVE IS TO IMPROVE THE CURRENT KNOWLEDGE OF INSTABILITY IN COMPRESSORS AND THEIR CONTROL BY CONSIDERING FOR THIS PURPOSE A HIERARCHY OF PHYSICAL MODELS OF INCREASING COMPLEXITY THAT PRESENT THIS TYPE OF INSTABILITY: A ROTOR CASCADE AS WELL AS A ROTOR-STATOR STAGE CONSISTING OF AN ARBITRARY NUMBER OF BLADES, INCLUDING REALISTIC MODELS FOR ADMISSION AND DISCHARGE. USING NUMERIC CODES SPECIFICALLY DESIGNED FOR THIS TASK, WE WILL FOCUS ON THE DETAILS OF THE PHYSICAL PHENOMENA THAT WILL TAKE PLACE AT THE LEVEL OF THE ALABE AS WELL AS THOSE RESULTING FROM INTERACTION WITH ADJACENT WINGS. THESE STUDIES ARE EXPECTED TO IMPROVE THE CURRENT KNOWLEDGE OF THESE INSTABILITYS AND THEIR SENSITIVITY TO CURRENT MANIPULATION, SUCH AS USING ACTUATORS OR CHANGES IN GEOMETRIA. THE INFORMATION OBTAINED IN THESE STUDIES WILL BE INCORPORATED IN PROBLEMS OF NUMERIC OPTIMISATION, BASED ON THE ASSISTANT OPERATOR, ORIENTED TO THE IMPROVEMENT OF THE STABILITY MARGIN IN AXIAL COMPRESSORS. (English) / qualifier | |||||||||||||||
point in time: 12 October 2021
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Revision as of 13:33, 12 October 2021
Project Q3141364 in Spain
| Language | Label | Description | Also known as |
|---|---|---|---|
| English | No label defined |
Project Q3141364 in Spain |
Statements
80,150.4 Euro
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100,188.0 Euro
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80.0 percent
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30 December 2016
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29 December 2020
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UNIVERSIDAD DE CADIZ
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36°29'40.92"N, 6°16'2.50"W
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11012
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POR MOTIVOS DE EFICIENCIA, LOS COMPRESORES AXIALES DE MOTORES AERONAUTICOS OPERAN TIPICAMENTE A ALTAS RELACIONES DE COMPRESION. SIN EMBARGO, A PARTIR DE UN CIERTO UMBRAL, ESTOS DISPOSITIVOS PRESENTAN NUMEROSAS INESTABILIDADES, TALES COMO LAS DENOMINADAS "SURGE" Y "ROTATING STALL", QUE COMPROMETEN SU INTEGRIDAD MECANICA. ACTUALMENTE, LA DESCRIPCION DE LOS PROCESOS FISICOS QUE PRODUCEN ESTAS INESTABILIDADES ES TODAVIA INCOMPLETA, ESPECIALMENTE EN EL CASO DE COMPRESORES DE ALTA VELOCIDAD. POR EJEMPLO, LA CONEXION ENTRE LOS DISTINTOS MECANISMOS DE INESTABILIDAD ES PARCIALMENTE DESCONOCIDA ASI COMO LO ES LA INFLUENCIA QUE LA GEOMETRIA DEL COMPRESOR TIENE EN LA APARICION DE ESTAS INESTABILIDADES (ALABES DE GUIA, PERFIL DE LOS ALABES, JUEGO DEL ROTOR, CARTER E INTERACCION ROTOR-ESTATOR). UNA MEJOR COMPRESION DE ESTOS ASPECTOS ES NECESARIA PARA MEJORAR LA EFICIENCIA DE ESTOS DISPOSITIVOS SIN PROVOCAR LA APARICION DE INESTABILIDADES._x000D_ _x000D_ EL PRESENTE PROYECTO DE INVESTIGACION TRATA ASPECTOS FUNDAMENTALES DE LOS MECANISMOS FISICOS QUE DESENCADENAN INESTABILIDADES EN COMPRESORES AXIALES ASI COMO SU CONTROL MEDIANTE TECNICAS TEORICAS Y NUMERICAS RECIENTES PARA EL ESTUDIO DE LA ESTABILIDAD Y SENSIBILIDAD ASI COMO OPTIMIZACION NUMERICA._x000D_ _x000D_ SE PERSIGUEN DOS OBJETIVOS EN ESTE PROYECTO. EL PRIMERO ES EL DE DESARROLLAR Y VALIDAR HERRAMIENTAS COMPUTACIONALES EFICIENTES PARA LA REALIZACION DE ESTUDIOS DE ESTABILIDAD Y SENSIBILIDAD GLOBAL ASI COMO LA OPTIMIZACION AERODINAMICA DE FLUJOS NO ESTACIONARIOS EN TURBOMAQUINAS. EL SEGUNDO OBJETIVO ES EL DE MEJORAR EL CONOCIMIENTO ACTUAL DE LAS INESTABILIDADES EN COMPRESORES Y SU CONTROL CONSIDERANDO PARA ELLO UNA JERARQUIA DE MODELOS FISICOS DE COMPLEJIDAD CRECIENTE QUE PRESENTAN ESTE TIPO DE INESTABILIDADES: UNA CASCADA DE ROTOR ASI COMO UNA ETAPA DE ROTOR-ESTATOR CONSISTENTE EN UN NUMERO ARBITRARIO DE ALABES, INCLUYENDO MODELOS REALISTAS PARA LA ADMISION Y LA DESCARGA. UTILIZANDO CODIGOS NUMERICOS ESPECIFICAMENTE DISEÑADOS PARA ESTA TAREA, NOS CENTRAREMOS EN LOS DETALLES DE LOS FENOMENOS FISICOS QUE TENDRAN LUGAR A NIVEL DEL ALABE ASI COMO LOS RESULTANTES DE LA INTERACCION CON ALABES COLINDANTES. SE ESPERA QUE ESTOS ESTUDIOS MEJOREN EL CONOCIMIENTO ACTUAL DE ESTAS INESTABILIDADES Y SU SENSIBILIDAD A LA MANIPULACION DE LA CORRIENTE, COMO POR EJEMPLO UTILIZANDO ACTUADORES O CAMBIOS EN LA GEOMETRIA. LA INFORMACION OBTENIDA EN ESTOS ESTUDIOS SERA INCORPORADA EN PROBLEMAS DE OPTIMIZACION NUMERICA, BASADOS EN EL OPERADOR ADJUNTO, ORIENTADOS A LA MEJORA DEL MARGEN DE ESTABILIDAD EN COMPRESORES AXIALES. (Spanish)
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FOR EFFICIENCY REASONS, AXIAL COMPRESSORS OF AERONAUTICAL ENGINES TYPICALLY OPERATE AT HIGH COMPRESSION RATIOS. HOWEVER, FROM A CERTAIN THRESHOLD, THESE DEVICES PRESENT NUMEROUS INSTABILITY, SUCH AS THE SO-CALLED “SURGE” AND “ROTATING STALL”, WHICH COMPROMISE THEIR MECHANICAL INTEGRITY. CURRENTLY, THE DESCRIPTION OF THE PHYSICAL PROCESSES THAT PRODUCE THESE INSTABILITY IS STILL INCOMPLETE, ESPECIALLY IN THE CASE OF HIGH-SPEED COMPRESSORS. FOR EXAMPLE, THE CONNECTION BETWEEN THE VARIOUS MECHANISMS OF INSTABILITY IS PARTIALLY UNKNOWN AS IS THE INFLUENCE THAT THE COMPRESSOR GEOMETRIA HAS ON THE APPEARANCE OF THESE INSTABILITY (GUIDE WINGS, PROFILE OF THE BLADES, ROTOR GAME, CARTER AND ROTOR-STATOR INTERACTION). Better COMPRETION OF THESE ASPECTS IS NEED TO IMPROVE THE EFFECTION OF THESE DISPOSITIVES WITHOUT PROVIDED THE APARICTION OF INESTABILITIES._x000D_ _x000D_ The present PROJECT OF PROJECT FOR FUNDAMENTAL ASPECTS OF THE PHISIC MECHANISMES INFORMATION instability IN Axial COMPRESSOURS AS YOUR CONTROL MEDIANT TECHNICAL AND RECIENT TECHNICAL AND RECIENTS FOR THE STUDY OF STABILITY AND SENSIBILITY ASSISTANCE AS NUMMERICAL OPTIMISATION._x000D_ _x000D_ PERSIGUED TWO OBJECTIVES IN THIS PROJECT. THE FIRST IS TO DEVELOP AND VALIDATE EFFICIENT COMPUTATIONAL TOOLS FOR CONDUCTING STABILITY AND GLOBAL SENSITIVITY STUDIES AS WELL AS THE AERODYNAMIC OPTIMISATION OF NON-STATIONARY FLOWS IN TURBOMAQUINAS. THE SECOND OBJECTIVE IS TO IMPROVE THE CURRENT KNOWLEDGE OF INSTABILITY IN COMPRESSORS AND THEIR CONTROL BY CONSIDERING FOR THIS PURPOSE A HIERARCHY OF PHYSICAL MODELS OF INCREASING COMPLEXITY THAT PRESENT THIS TYPE OF INSTABILITY: A ROTOR CASCADE AS WELL AS A ROTOR-STATOR STAGE CONSISTING OF AN ARBITRARY NUMBER OF BLADES, INCLUDING REALISTIC MODELS FOR ADMISSION AND DISCHARGE. USING NUMERIC CODES SPECIFICALLY DESIGNED FOR THIS TASK, WE WILL FOCUS ON THE DETAILS OF THE PHYSICAL PHENOMENA THAT WILL TAKE PLACE AT THE LEVEL OF THE ALABE AS WELL AS THOSE RESULTING FROM INTERACTION WITH ADJACENT WINGS. THESE STUDIES ARE EXPECTED TO IMPROVE THE CURRENT KNOWLEDGE OF THESE INSTABILITYS AND THEIR SENSITIVITY TO CURRENT MANIPULATION, SUCH AS USING ACTUATORS OR CHANGES IN GEOMETRIA. THE INFORMATION OBTAINED IN THESE STUDIES WILL BE INCORPORATED IN PROBLEMS OF NUMERIC OPTIMISATION, BASED ON THE ASSISTANT OPERATOR, ORIENTED TO THE IMPROVEMENT OF THE STABILITY MARGIN IN AXIAL COMPRESSORS. (English)
12 October 2021
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Cádiz
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Identifiers
DPI2016-75777-R
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