Transcript ICLEAC 12 MONTH MEETING

ICLEAC Survey Presentation
Instability 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. Hernandez
Turbomeca
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ICLEAC Survey Presentation
4 year program started March 1 2000
ICLEAC Survey Presentation
Instability Control of Low Emission Aero-Engine Combustors
Partners
Mission
Organisation
Experiments and Measurements
Calculations
Exploitation and Dissemination
Questions
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ICLEAC Survey Presentation
Agenda
ICLEAC Partners
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F
D
D
F
UK
I
UK
F
F
UK
D
D
I
UK
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Turbomeca
MTU
Rolls-Royce Deutschland
Snecma
Rolls-Royce
AVIO S.p.A.
QINETIQ
CERFACS
CNRS/DR5/EM2C
Cranfield University
Karlsruhe University - EBI
Munich University - TDM
Genova University - DIMSET
UCAM-DENG
ICLEAC Mission
Low Emissions
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*
* Unsteady Reynolds Averaged Navier Stokes
* Large Eddy Simulation
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ICLEAC Survey Presentation
•
Combustion Instabilities
ICLEAC Mission
• 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
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ICLEAC Survey Presentation
Measurements
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
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ICLEAC Survey Presentation
•
ICLEAC Experiments and Measurements
‘2D’ atmospheric combustion rig
Loudspeakers
Microphones
• acoustic excitation
Adiabatic Walls
• modular design
• Optical access
• PLIF*, Chemiluminescence (OH,
CH, C2 radicals)
Optical Access
Hot Wire
• FTF derivation
FUEL INLET
* Planer Laser Induced Fluorescence
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
• ambient air temperature inlet
ICLEAC Experiments and Measurements
• 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
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Atmospheric Injector Spray
Rig
ICLEAC Experiments and Measurements
Injector spray test rig
• 300-500 K
• Acoustic excitation
• Optical access
• PDA and LSD for droplet size,
velocity, and concentration
measurement in dense sprays
• Spray FTF derivation
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
• 3 bar
ICLEAC Experiments and Measurements
• Atmospheric
• Acoustic excitation
• Optical access
• LDV*, PIV*
• Derivation of 3D
velocity field and
turbulence
* Laser Doppler Velocimetry
* Particle Imaging Velocimetry
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Large scale injector test
rig
ICLEAC Experiments and Measurements
Atmospheric Combustion Rig
q u a rtz glass
c h am b er
• Acoustic excitation
• Optical access
• OH Chemiluminescence
• FTF derivation
a x ial v a n e
sw irl g e n e ra to r
a ir in let
(p ilo t flam e)
n a tu ral g a s
ta n g en tial in lets
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ICLEAC Survey Presentation
• T3 770 K
ICLEAC Experiments and Measurements
Rig
• T3 800 K
• Acoustic excitation
• Optical access
• PIV, Mie scattering, OH Chemiluminescence
• Derivation of flow/spray field and FTF
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Atmospheric Combustion
ICLEAC Experiments and Measurements
•P3 40 bar
•T3 800 K
•Acoustic excitation
•Optical access
•PIV, OH Chemiluminescence
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ICLEAC Survey Presentation
High Pressure
Combustion Rig
ICLEAC Experiments and Measurements
Atmospheric &
High Pressure
Combustion Rig
LPP Burner
Airflow
Silencer
• P3 15 bar
• T3 800 K
• Acoustic excitation
Combustor
Internal ductwork
Variable frequency
Siren
• FTF derivation from fast response
pressure measurements and CH
Chemiluminescence
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CH sampling
probe
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ICLEAC Survey Presentation
Pressure casing
Pressure
measurement
ICLEAC Calculations
• Gives frequency and stability predictions
• Fast enough to be used at design stage
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ICLEAC Survey Presentation
Low-Order Model
• Linear model for combustion instability
ICLEAC Calculations
CFD applied to rumble
ICLEAC Survey Presentation
• Mechanism of self-excited oscillation
• Identification of flame transfer function
Pressure
• Integration of CFD and low-order models
Time
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Exploitation and Dissemination
RR-UK & RRD
LPP modules
• delay time
• effective area
Air blast burners
Flame characterization
• Flame transfer functions
• Spray transfer functions
CRANFIELD / QINETIQ / TD-Munich
ICLEAC
UCAM
RR-UK large engines
RRD
medium engines
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CFD simulations
• 2D & 3D geometries
• numerical FTF
• self-excitation
LOM
• 1D geometry
• implementation of FTF
• validation
CFD simulations
• in-house application
• best practice
• validation
Multi-Link Flow Network
• in-house application
• integration of LOM
• validation
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Single sector test rigs
• atmospheric
• low pressure < 3 bar
• intermediate pressure < 15 bar
Exploitation and Dissemination Example
LOM results of RB211 DLE industrial combustion system
x (m)
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Unstable Mode
Frequency
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Combustor Mode
Exploitation and Dissemination
AVIO S.p.A
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
UNIGE-DIMSET: Experimental activities
ICLEAC
UNIGE-DIMSET: Numerical activities
Unsteady CFD Solver NastComb:
•in-house development &
validation
•advanced turbulence model
•reactive prediction (detailed)
•radiation modelling
AVIO S.p.A
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Analysis mode (large scale
premixer):
• comparison of flow fields
and unstable behaviour
• critical modes detection
• parametric optimisation
URANS Transient Performance
Method (TPM) applied to gas
turbine combustor development
Design mode (Real LPP
prototype):
• preheated 2-phase behaviour
• fully reactive conditions
• Transient Performance
Method (CFD based)
• LPP double swirler injector design
• RANS code for design and analysis
validation
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Laboratory
• LPP double swirler injector of
AVIO design
• large scale model
• same Re number
• original and modified
geometries
1.2
Exploitation and Dissemination Example
Transient Performance Method : F Function
1
Extended Outlet Premixer
0.8
rms (K )
Kout
Scale 1:1
B.C. : 6 bar - 760 K
Scale 1:1
0.6
6 bar - 760K
Combustion
0.4
0.2
Swirler Ext/Int Mass Flow
Modified
0
0.0E+00
-0.2
5.0E+04
1.0E+05
Inlet Conditions : 760 K
1.5E+05
2.0E+05
2.5E+05
3.0E+05
3.5E+05
4.0E+05
Iterations
Time-Dependent Numerical Prediction of the Flow Within an Aero-Propulsion Combustion System
ICLEAC 42-Month Expert Meeting - October 15th, 2003 - Pomigliano d’Arco (Naples)
Pittaluga F.; Traverso S. - UNIGE - DIMSET
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4.5E+05
5.0E+05
5.5E+05
ICLEAC Survey Presentation
F=
Experimental Test Rig
Exploitation and Dissemination
Turbomeca & SNECMA
Measurements
• PIV
• OH chem.
• Hot wire anemometry
Flame Characterisation
•Transfer functions
• velocity profiles
• visualisation, ...
EM2C
ICLEAC
CERFACS
SNECMA
Turbomeca
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LES modelling
results
LES model
development
LES modelling applied to gas
turbine combustor
development
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Laboratory rig
• non-premixed
• turbulent burner
Exploitation and Dissemination Example
LES calculation of CNRS/EM2C 2D burner
Velocity field
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Propane iso-surface
(YC3H8=0.06 stoichiometric
value)
coloured by the temperature
Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Transverse cuts coloured
by the propane consumption rate
Exploitation and Dissemination Example
LES calculation of CNRS/EM2C 2D burner
Movie of forced case
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ICLEAC Survey Presentation
Simulation time 21ms ( one flow-through time)
Questions
ICLEAC Survey Presentation
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Acronyms
D escrip tion
AFR
DOE
KBE
LBO
LDP
LDV
LES
L IF
L II
LPP
LSD
PDA
PDPA
PF
P IV
P L IF
RANS
SM D
URANS
A ir F uel R atio
D esign O f E xperim ent
K now ledge B ased E ngineering
L ean B low O ut
L aser D opler
L aser D opler V elo cim etry
L arge E ddy S im ulation
L aser Indu ced F luorescence
L aser Indu ced In cand escence
L ean P rem ixed P rev aporised
L aser S heet D ropsizing
P hase D opler A n em otry
P hase D oppler P article A nalyser
P attern F actor
P article Im aging V elo cim etry
P laner L aser Induced F luorescen ce
R eynolds A verag ed N avier-S tokes
S auter M ean D iam eter
U nsteady R eynolds A veraged N avier-S tokes
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ICLEAC Survey Presentation
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A cron ym
ICLEAC Organisation
In each Work package we have two types of hardware that
are investigated :
• generic / academic hardware
• real scale / Low Emission Aero Engine hardware.
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ICLEAC Survey Presentation
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
ICLEAC Experiments and Measurements
• T3 650 K
• Optical access
• Acoustic excitation
• Dynamic pressure, CH Chemiluminescence
• FTF derivation
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Stuttgart, 13/14 November 2003
ICLEAC Survey Presentation
Atmospheric
Combustion Rig
ICLEAC Experiments and Measurements
• P3 15 bar
• T3 800 K
• Acoustic excitation
• Dynamic pressure, CH Chemiluminescence
• FTF derivation
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ICLEAC Survey Presentation
High Pressure
Combustion Rig
ICLEAC Mission
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ICLEAC Survey Presentation
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.