TIDE

Tangential Impulse Detonation Engine

Coordinatore	INSTITUTUL NATIONAL DE CERCETARE-DEZVOLTARE TURBOMOTOARE - COMOTI    more  Organization address address: "IULIU MANIU AVENUE 220D, SECTOR 6" city: BUCHAREST 6 postcode: 61126 contact info Titolo: Mr. Nome: Trifu Cognome: Leonard Email: send email Telefono: +40 723557519 Fax: +40 214340241
Nazionalità Coordinatore	Romania [RO]
Totale costo	809˙656 €
EC contributo	599˙805 €
Programma	FP7-TRANSPORT Specific Programme "Cooperation": Transport (including Aeronautics)
Code Call	FP7-AAT-2012-RTD-L0
Funding Scheme	CP-FP
Anno di inizio	2013
Periodo (anno-mese-giorno)	2013-08-01   -   2015-07-31

 Partecipanti

#	participant	country	role	EC contrib. [€]
1	INSTITUTUL NATIONAL DE CERCETARE-DEZVOLTARE TURBOMOTOARE - COMOTI  Organization address address: "IULIU MANIU AVENUE 220D, SECTOR 6" city: BUCHAREST 6 postcode: 61126 contact info Titolo: Mr. Nome: Trifu Cognome: Leonard Email: send email Telefono: +40 723557519 Fax: +40 214340241	RO (BUCHAREST 6)	coordinator	220˙150.00
2	LUNDS UNIVERSITET  Organization address address: Paradisgatan 5c city: LUND postcode: 22100 contact info Titolo: Prof. Nome: Johan Cognome: Revstedt Email: send email Telefono: +46 46 2224302	SE (LUND)	participant	195˙680.00
3	INSTITUT VON KARMAN DE DYNAMIQUE DES FLUIDES  Organization address address: CHAUSSEE DE WATERLOO 72 city: RHODE SAINT GENESE postcode: 1640 contact info Titolo: Mr. Nome: Dominick Cognome: Hemeryck Email: send email Telefono: +32 2 3599617 Fax: +32 2 3599600	BE (RHODE SAINT GENESE)	participant	133˙975.00
4	Institute of Applied Physics of the Academy of Sciences of Moldova  Organization address address: Academiei 5 city: Chisinau postcode: MD2028 contact info Titolo: Mr. Nome: Cuciuc Cognome: Tudor Email: send email Telefono: 37360226707 Fax: 37322738149	MD (Chisinau)	participant	50˙000.00

Mappa

 Word cloud

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 Obiettivo del progetto (Objective)

'The proposed project aims at designing, manufacturing and building of a demonstrator for a new engine concept. The new concept replaces the usual turbine of a classical turboengine by a number of Pulse Detonation Combustors (PDC) placed on a disk that rotates under the tangential impulse provided by the exhaust jet of the PDC. The rotating disk is coupled, through a shaft, to the compressor that is placed upstream of the PDC in order to raise its inlet pressure. Two solutions will be considered for the engine propulsion: a propeller, coupled, via a gearbox, to the PDC shaft, or by using the reactive thrust of the PDC exhaust jet, directed at an optimal angle. The PDC inlet with be equipped with aerodynamic valves that control the air entrance into the PDC, thus allowing a significant increase in the detonation frequency, allowing for noise reduction and reduced dimensions. The demonstrator, consisting of a single, fixed, PDC equipped with a fuel injection and ignition system designed for the requirements of the engine concept, will be tested on an experimental facility in order to demonstrate the PDC capability to provide enough power to meet the requirements of the compressor, with sufficient reserve for powering to propel the host aircraft. The project also proposes the design and numerical simulation of the engine compressor, adapted to the requirements of the new engine, most importantly the high vibration load and oscillatory back pressure under which the compressor operates. A last objective of the project is to provide a full definition of the engine constructive solution and a numerical simulation of the flow through the engine that will allow the estimation of the engine performances. The new emerging technology is expected to provide a significant increase in the engine's thermodynamic cycle maximum temperature and efficiency, a drastic reduction in its weight and specific fuel consumption, and a decrease of greenhouse gas emissions.'