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Turboshaft Engine Exhaust Noise Identification

PROJECTS
Funding
European
European Union
Duration
-
Status
Complete with results
Geo-spatial type
Other
Total project cost
€4 686 637
EU Contribution
€3 297 418
Project website
Project Acronym
TEENI
STRIA Roadmaps
Vehicle design and manufacturing (VDM)
Transport mode
Airborne icon
Transport policies
Environmental/Emissions aspects,
Decarbonisation
Transport sectors
Passenger transport,
Freight transport

Overview

Call for proposal
FP7-AAT-2007-RTD-1
Link to CORDIS
Background & Policy context

TEENI dealt with experimental identification of engine modules' contribution on exhaust Broadband Noise emission. This noise component is the second most dominant noise source of Turboshaft engines, and installing acoustic liners on the exhaust can lead to significant benefits in reducing helicopter noise levels.

Turboshaft exhaust noise consists of a mix of combustion and turbine noise, with very little jet noise. It is representative of what is generally known as core noise on aircraft engines and can help in understanding this complicated subject matter because of its simpler geometry and absence of parasitic noise sources (such as jet and fan noise).

Objectives

The TEENI work programme was divided into three interdependent Workpackages (WP):

  • WP1: Innovative sensors development - to provide reference measurements of fluctuating quantities within the engine under harsh operating conditions;
  • WP2: Noise Sources Breakdown Techniques (NSBT) development - to determine the dominant emission location(s) from external measurements. Several techniques were evaluated, both internal and external measurements were carried out, and various formalisms and approaches were considered. Propagation through turbine(s) and tools to help take into account individual engine noise sources were also developed;
  • WP3: An Ardiden 1H Turboshaft engine full-scale test - to include and test the developed sensors, to verify (through correlation with internal sensors) and to assess the pertinence of the various NSBT, and to provide an initial example of noise decomposition per module.

In order to reduce development risks, both sensors and methods were tested within their relative WP before the engine test.

Methodology

TEENI's major deliverables were:

  • A set of sensors for measuring unsteady quantities, suitable for full-scale engine testing (650°<T<1000°C);
  • A noise breakdown technique selected from a set of methods as a result of comparisons with data from an engine noise database;
  • A thorough understanding of noise generation, propagation and radiation through the exhaust;
  • A comprehensive full-scale engine test database;
  • A ranking of exhaust noise sources, with a recommendation on the noise source to be reduced in priority, through appropriately tuned liners in the exhaust duct.

Funding

Parent Programmes
Institution Type
Public institution
Institution Name
The European Commission
Type of funding
Public (EU)
Other Programme
Programme acronym or name (optional)
Funding Source
Information about the funding institution (optional)

Results

The second dominant noise source of a Turboshaft engine is the noise component of engine modules. Installing acoustic liners on the exhaust can lead to considerable noise benefits on helicopter noise levels. The project suffered from a poor estimation of possible difficulties arising from the implementation of new instrumentation for the engine. As a result, many of the components used for the implementation had to be built from scratch which required the project to be extended from 3 years to 5 years. During the testing phase, the noise reduction components and the newly installed instrumentation proved successful.

TEENI's main deliverables were:

  • Pressure and Temperature Probes measuring unsteady quantities, equipped for engine testing (6501400 degrees Celsius), with a bandwidth of more than 4kHz for Pressure Probes and a bandwidth of more than 1 kHz for Thermocouples.
  • The first-ever comprehensive full-scale engine test database for this type of testing, with extensive internal measurements and farfield instrumentation.
  • Development of a panel of original signal processing methods during the project, which realised noise breakdown by using internal measurements to understand the origin of noise measured in the farfield.
  • Elements of understanding noise generation, propagation, and radiation through the exhaust.

Combustion noise was identified at low frequencies; the relative importance of this increasing after the HP Turbine. Broadband noise origin for frequencies above 2kHz were not fully explained.

Innovation aspects

First database of its kind, made for registering results of testing for broadband noise emission.

Development of new components and instrumentations.

Technical Implications

Further testing is needed, but the project was a step towards the development of components and instruments that can reduce broadband noise emissions considerably.

Strategy targets

1. Innovating for the future, technology and behaviour: The reduction of broadband noise emissions helps create a better urban environment, as it reduces noise pollution that could be both disturbing and damaging.

2. Modern infrastructure and smart funding: Aviation is a part of modern infrastructure, and as such the project has helped develop tools for improving aviation technology for the benefit of both cargo and passenger transport.

Partners

Lead Organisation
Organisation
Safran Helicopter Engines
Address
Avenue Du President Szydlowski, 64510 Bordes, France
EU Contribution
€456 953
Partner Organisations
Organisation
Inasco Hellas Etaireia Efarmosmenon Aerodiastimikon Epistimon Ee
Address
Napoleontos Zerva 18, 16675 Glyfada Athina, Greece
EU Contribution
€159 000
Organisation
The Provost Fellows And Scholars Of The College Of The Holy And Undivided Trinity Of Queen Elizabeth Near Dublin (Hereinafter Called Tcd)
Address
College Green, DUBLIN, 2, Ireland
Organisation website
EU Contribution
€302 201
Organisation
"institutul National De Cercetare-Dezvoltare Aerospatiala ""elie Carafoli""- Incas Bucuresti"
Address
SECTOR 6, B-DUL IULIU MANIU NR. 220, 061126 BUCURESTI, Romania
Organisation website
EU Contribution
€500 250
Organisation
Ecole Polytechnique Fédérale De Lausanne
Address
Batiment Ce 3316 Station 1, 1015 LAUSANNE, Switzerland
Organisation website
EU Contribution
€295 432
Organisation
Bruel & Kjaer Sound & Vibration Measurement A/s
Address
Skodsborgvej 307, 2850 Naerum, Denmark
Organisation website
EU Contribution
€130 350
Organisation
Office National D'etudes Et De Recherches Aerospatiales
Address
CHEMIN DE LA HUNIERE, 91120 PALAISEAU, France
Organisation website
EU Contribution
€198 678
Organisation
Deutsches Zentrum Fr Luft Und Raumfahrt E.v
Address
Linder Hoehe, 51147 KOELN, Germany
Organisation website
EU Contribution
€500 994
Organisation
Anotec Consulting Sl
Address
Calle Rector Jose Vida Soria 7-2, 18600 Motril Granada, Spain
EU Contribution
€95 560
Organisation
Avio S.p.a.
Address
Via 1 Maggio 99, 00187 RIVALTA DI TORINO, Italy
Organisation website
EU Contribution
€94 000
Organisation
Microflown Technologies Bv
Address
Tivolilaan 205, 6824 BV Arnhem, Netherlands
EU Contribution
€564 000

Technologies

Technology Theme
Sensor technologies
Technology
Integrated sensors for structural components
Development phase
Validation
Technology Theme
Noise testing, modelling and reduction
Technology
Aircraft noise reduction at source
Development phase
Validation

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