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CORNET

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CORE NOISE ENGINE TECHNOLOGY

Lean burn combustor technologies introduced to reduce NOx emissions are proving to be inherently noisier than conventional combustors, generating broadband noise that can be heard external to the aircraft. Without careful design a... see more

30/04/2019

THE CHANCELLOR MAS...

998K€

Project Budget: 998K€

Project leader

THE CHANCELLOR MASTERS AND SCHOLARS OF THE UN... No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

PARTICIPATION DEPralty Sin fecha límite de participación.

Ver 4 Participantes

Financing granted El organismo H2020 notifico la concesión del proyecto The day 2019-04-30

JTI-CS2-2014-CFP01-ENG-03-02: Advanced analytical tool for the un... Scope:The current proposal is aimed at understanding the flow physics involved in the generation and...

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Cerrada does 10 years

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Este proyecto no cuenta con búsquedas de partenariado abiertas en este momento.

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No hay información privada compartida para este proyecto. Habla con el coordinador.

4 Participantes

THE CHANCELLOR MASTERS AND S...

519.99K€ | Leader

S.A. DE VERA

525.25K€ | participant

DLR

377.78K€ | participant

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Project duration: 38 months Date Start: 2016-02-18
End date: 2019-04-30

Project leader

THE CHANCELLOR MASTERS AND SCHOLARS OF THE UN... No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Project Budget 998K€

participation deadline Sin fecha límite de participación.

Project description Lean burn combustor technologies introduced to reduce NOx emissions are proving to be inherently noisier than conventional combustors, generating broadband noise that can be heard external to the aircraft. Without careful design and optimisation, there is a danger the low emission cores will cause the aircraft engines to exceed the Horizon 2020 noise requirement. The research in the CORNET proposal is aimed at understanding the flow physics involved in the generation and propagation of core noise in low emission cores. It includes both the ‘direct noise’ of combustion, pressure waves generated directly by unsteadiness in the rate of combustion, and the ‘indirect noise’ generated as entropy waves accelerate through the Nozzle Guide Vanes (NGVs) at combustor exit and propagate through turbine blade rows. Large Eddy Simulations of a combustor with a realistic engine fuel injector operating at representative engine conditions are validated through high-speed optical diagnostics applied to a high-pressure rig. The combustor modelling gives the entropy and acoustic waves incident on the NGVs. The generation of in-direct noise is predicted through unsteady high-resolution computations of the interaction of these entropy and acoustic waves within a high-pressure turbine stage. The new understanding will be captured in an advanced analytical combustion noise prediction tool that can be readily used by industry.

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