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Intermediate Compressor Case Duct Aerodynamics

To reduce fuel-burn and CO2 emissions from aero gas turbines innovative, very-high bypass ratio and smaller ultra-high pressure ratio core engine technologies are required as this will increase their propulsive and thermal efficie... ver más

30/04/2021

LOUGHBOROUGH UNIVE...

513K€

Presupuesto del proyecto: 513K€

Líder del proyecto

LOUGHBOROUGH UNIVERSITY No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Fecha límite participación Sin fecha límite de participación.

Ver 2 Participantes

Financiación concedida El organismo H2020 notifico la concesión del proyecto el día 2021-04-30

JTI-CS2-2017-CFP06-ENG-03-19: Intermediate Compressor Case Duct A...

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Cerrada hace 7 años

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Información adicional privada

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

2 Participantes

LOUGHBOROUGH UNIVERSITY

387.88K€ | Lider

CHALMERS TEKNISKA HOGSKOLA A...

125.36K€ | Participante

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Duración del proyecto: 38 meses Fecha Inicio: 2018-02-12
Fecha Fin: 2021-04-30

Líder del proyecto

LOUGHBOROUGH UNIVERSITY No se ha especificado una descripción o un objeto social para esta compañía.

TRL 4-5

Presupuesto del proyecto 513K€

Fecha límite de participación Sin fecha límite de participación.

Descripción del proyecto To reduce fuel-burn and CO2 emissions from aero gas turbines innovative, very-high bypass ratio and smaller ultra-high pressure ratio core engine technologies are required as this will increase their propulsive and thermal efficiency. However, this makes the design of the intermediate compressor ducts connecting the various compressor spools much more challenging as the change in radius becomes much greater. The ability to design shorter, more aggressive ducts is advantageous from a performance and weight saving perspective but flow separation must be avoided if efficiency is not to be compromised or the downstream compressor performance not adversely affected. This programme of work will establish and validate improved and more integrated duct technologies that will contribute to the development of the very-high bypass ratio turbo fan demonstrator (UltraFan™). A fully annular, low-speed test facility incorporating a representative compressor stage will be used to validate, at low TRL, an initial compressor inter duct design. A representative bleed port will also be added upstream of the compressor to allow compressor/bleed/duct interactions to be studied. This bleed port is required in the engine to extract ice and water but currently little is known about how it affects the compressor or duct aerodynamics. The results will be used to develop and experimentally validate future potential duct technologies for the UltraFan™ engine and other very high bypass ratio applications. This will include a second design solution optimised for a more effective bleed extraction and/or lower impact on system performance and stall margin. In parallel to the experimental work this project will also establish best practice for advanced, yet efficient, CFD methods (e.g. hybrid RANS/LES). The experimental data will be used to validate these methodologies which will provide increased numerical accuracy but with a reasonable turn-over time and robust performance.

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