icleac survey presentation i nstability c ontrol of l ow e mission a ero-engine c ombustors

ICL

EA

C S

urvey P

resentatio

n

Stuttgart, 13/14 November 20031

ICLEAC Survey PresentationInstability Control of Low Emission Aero-Engine Combustors

G4RD-CT-2000-0215

R&T project within the 5th Framework program of the European Union:

Presented by:L. HernandezTurbomeca

4 year program started March 1 2000

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Survey PresentationInstability Control of Low Emission Aero-Engine Combustors

Agenda

Partners

Mission

Organisation

Experiments and Measurements

Calculations

Exploitation and Dissemination

Questions

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Partners

Turbomeca F

MTU D

Rolls-Royce Deutschland D

Snecma F

Rolls-Royce UK

AVIO S.p.A. I

QINETIQ UK

CERFACS F

CNRS/DR5/EM2C F

Cranfield University UK

Karlsruhe University - EBI D

Munich University - TDM D

Genova University - DIMSET I

UCAM-DENG UK

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Mission

Low Emissions Combustion Instabilities

* Unsteady Reynolds Averaged Navier Stokes* Large Eddy Simulation

• Treatment of CI today: a posteriori– expensive and time consuming

• re-design• tests

• Objective: being able to deal with the problem a priori– Concept phase

• Design Rules• Low Order Models

– Development phase• Heavy CFD methods: URANS* and LES*

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Mission

Measurements• Injector Aerodynamics and spray databases (steady and unsteady)• Flame Transfer Functions (FTF) in simple and engine like sector rigs• Generic and real engine geometry thermo acoustics and mixing

Calculations• FTF calculated by URANS and LES• URANS and LES development

Tools• Design rules• Low Order Model (LOM)• URANS and LES

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Organisation

5 Work Packages

• WP1 Management and exploitation

• WP2 Unsteady behaviour of Fluid-dynamic LP*/LPP* injection systems

• WP3 Measurement of Transfer Functions

• WP4 Combustion Instabilities Prediction

• WP5 Advanced 2 and 3D diagnostics on combustors

4 year program started March 1 2000

• Final report April 2004

* Lean Premixed* Lean Pre-vaporised Premixed

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Experiments and Measurements

‘2D’ atmospheric combustion rig

• ambient air temperature inlet

• acoustic excitation

• modular design

• Optical access

• PLIF*, Chemiluminescence (OH, CH, C2 radicals)

• FTF derivation

* Planer Laser Induced Fluorescence

Loudspeakers

Microphones

Adiabatic Walls

Optical AccessHot Wire

FUEL INLET

ICL

EA

C S

urvey P

resentatio

n



Atmospheric Injector SprayRig

• Optical access

• Acoustic excitation

• PDA* and LSD* for droplet size, velocity, and concentration measurement in dense sprays

• Spray FTF derivation

* Phase Doppler Anemometry * Laser Sheet Drop sizing

ICL

EA

C S

urvey P

resentatio

n



Injector spray test rig

• 3 bar

• 300-500 K


• Optical access• PDA and LSD for droplet size,

velocity, and concentration measurement in dense sprays

• Spray FTF derivation

ICL

EA

C S

urvey P

resentatio

n



Large scale injector testrig

• Atmospheric


• Optical access

• LDV*, PIV*

• Derivation of 3D velocity field and turbulence

* Laser Doppler Velocimetry * Particle Imaging Velocimetry

ICL

EA

C S

urvey P

resentatio

n



Atmospheric Combustion Rig

• T3 770 K


• Optical access

• OH Chemiluminescence

• FTF derivationaxial vaneswirl generator

quartz glass

natural gastangential inlets

air inlet(pilot flame)

chamber

ICL

EA

C S

urvey P

resentatio

n



Atmospheric Combustion

Rig

• T3 800 K


• Optical access

• PIV, Mie scattering, OH Chemiluminescence

• Derivation of flow/spray field and FTF

ICL

EA

C S

urvey P

resentatio

n



High PressureCombustion Rig

•P3 40 bar

•T3 800 K

•Acoustic excitation

•Optical access

•PIV, OH Chemiluminescence

ICL

EA

C S

urvey P

resentatio

n



Atmospheric & High PressureCombustion Rig

• P3 15 bar

• T3 800 K


• FTF derivation from fast response pressure measurements and CH Chemiluminescence

Airflow

Pressure casing

Pressure measurement

LPP Burner

Internal ductworkVariable frequency

Siren

CH sampling probe

Combustor

Silencer

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Calculations

Low-Order Model

• Linear model for combustion instability

• Gives frequency and stability predictions

• Fast enough to be used at design stage

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Calculations

CFD applied to rumble

• Mechanism of self-excited oscillation

• Identification of flame transfer function

• Integration of CFD and low-order models

TimeP

ress

ure

ICL

EA

C S

urvey P

resentatio

n


Exploitation and DisseminationRR-UK & RRD

Single sector test rigs• atmospheric• low pressure < 3 bar• intermediate pressure < 15 bar

LPP modules• delay time• effective areaAir blast burners

Flame characterization• Flame transfer functions• Spray transfer functions

LOM• 1D geometry• implementation of FTF• validation

Multi-Link Flow Network• in-house application• integration of LOM• validation

CFD simulations• 2D & 3D geometries• numerical FTF• self-excitation

CFD simulations• in-house application• best practice• validation

CRANFIELD / QINETIQ / TD-Munich

UCAM

RR-UK large enginesRRD medium engines

ICLEAC

ICL

EA

C S

urvey P

resentatio

n


Exploitation and Dissemination ExampleLOM results of RB211 DLE industrial combustion system

Frequency

Unstable ModeCombustor Mode

x (m)

ICL

EA

C S

urvey P

resentatio

n


Exploitation and DisseminationAVIO S.p.A

Laboratory•LPP double swirler injector of AVIO design

• large scale model• same Re number•original and modified geometries

Analysis mode (large scale premixer):• comparison of flow fields and unstable behaviour• critical modes detection• parametric optimisation

UNIGE-DIMSET: Experimental activities

Measurement techniques•3D LDV•hot-wire anemometry•PIV

Unsteady aerodynamic investigation•Time averaged and ensemble averaged flow field

•Reynolds stress distributions•unsteady phenomena detection•data sets for time-dependent N.S. and RANS code assessment

Design mode (Real LPP prototype):

• preheated 2-phase behaviour• fully reactive conditions• Transient Performance Method (CFD based)

ICLEAC

AVIO S.p.A URANS Transient Performance Method (TPM) applied to gas turbine combustor development

•LPP double swirler injector design•RANS code for design and analysis validation

Unsteady CFD Solver NastComb:•in-house development & validation•advanced turbulence model•reactive prediction (detailed) •radiation modelling

UNIGE-DIMSET: Numerical activities

ICL

EA

C S

urvey P

resentatio

n


Exploitation and Dissemination Example

IterationsIterations

TTransient ransient PPerformance erformance MMethod ethod : : Function FunctionF

-0.2

0

0.2

0.4

0.6

0.8

1

1.2

0.0E+00 5.0E+04 1.0E+05 1.5E+05 2.0E+05 2.5E+05 3.0E+05 3.5E+05 4.0E+05 4.5E+05 5.0E+05 5.5E+05

( )outK

Krms=F

Experimental Test Rig

Extended Outlet Premixer

Swirler Ext/Int Mass FlowModified

Inlet Conditions : 760 K

Scale 1:1

B.C. : 6 bar - 760 K

Scale 1:1

6 bar - 760K

CombustionCombustion

Time-Dependent Numerical Prediction of the Flow Within an Aero-Propulsion Combustion SystemICLEAC 42-Month Expert Meeting - October 15th, 2003 - Pomigliano d’Arco (Naples)

Pittaluga F.; Traverso S. - UNIGE - DIMSET

ICL

EA

C S

urvey P

resentatio

n


Exploitation and DisseminationTurbomeca & SNECMA

Laboratory rig• non-premixed• turbulent burner

LES model development

EM2C

CERFACS

Measurements• PIV• OH chem.• Hot wire anemometry

Flame Characterisation •Transfer functions• velocity profiles• visualisation, ...

LES modelling results ICLEAC

SNECMA LES modelling applied to gas turbine combustor developmentTurbomeca

ICL

EA

C S

urvey P

resentatio

n


Exploitation and Dissemination ExampleLES calculation of CNRS/EM2C 2D burner

Velocity fieldPropane iso-surface (YC3H8=0.06 stoichiometric value) coloured by the temperature

Transverse cuts coloured by the propane consumption rate

ICL

EA

C S

urvey P

resentatio

n


Exploitation and Dissemination ExampleLES calculation of CNRS/EM2C 2D burner

Simulation time 21ms ( one flow-through time)

Movie of forced case

ICL

EA

C S

urvey P

resentatio

n


Questions

ICL

EA

C S

urvey P

resentatio

n


Acronyms

Acronym DescriptionAFR Air Fuel RatioDOE Design Of ExperimentKBE Knowledge Based EngineeringLBO Lean Blow OutLDP Laser DoplerLDV Laser Dopler VelocimetryLES Large Eddy SimulationLIF Laser Induced FluorescenceLII Laser Induced IncandescenceLPP Lean Premixed PrevaporisedLSD Laser Sheet DropsizingPDA Phase Dopler AnemotryPDPA Phase Doppler Particle AnalyserPF Pattern FactorPIV Particle Imaging VelocimetryPLIF Planer Laser Induced FluorescenceRANS Reynolds Averaged Navier-StokesSMD Sauter Mean DiameterURANS Unsteady Reynolds Averaged Navier-Stokes

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Organisation

WP2 : isothermal experiments on injection systems

WP3 : transfer functions on combustors - effect of damping technologies

WP4 : development of simulation methods

WP5 : detailed measurements on combustors

In each Work package we have two types of hardware thatare investigated :• generic / academic hardware• real scale / Low Emission Aero Engine hardware.

ICL

EA

C S

urvey P

resentatio

n



AtmosphericCombustion Rig

• T3 650 K

• Optical access


• Dynamic pressure, CH Chemiluminescence

• FTF derivation

ICL

EA

C S

urvey P

resentatio

n



High PressureCombustion Rig

• P3 15 bar

• T3 800 K


• Dynamic pressure, CH Chemiluminescence

• FTF derivation

ICL

EA

C S

urvey P

resentatio

n


ICLEAC Mission

To understand fundamental mechanisms leading to Combustion Instabilities in Aero Engine Low Emission Combustors. This includes the elaboration of comprehensive databases on academic flames and real combustor flames used both for analysis and code validation

To develop and validate predictive tools on generic and real Low Emission combustors also used in other programmes. This includes RANS and LES methods as well as a low order model (TALON) that is delivered to the partners during the last year of the programme

To define and validate design rules for Low Emission Combustors for Aero Engines to avoid/reduce combustion instabilities. Includes correlations between combustor geometries, and oscillation frequencies / amplitudes.

icleac survey presentation i nstability c ontrol of l ow e mission a ero-engine c ombustors

Documents