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Multi-objective optimization of a
centrifugal compressor for turbocharging
Johannes RatzGas Turbines and Aerospace Propulsion
TU Darmstadt
Source:
MTU Friedrichshafen GmbH
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Contents
2Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
Optimization-Workflow
Results
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Introduction
3Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
Source:
MTU Friedrichshafen GmbH
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Introduction
4Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
Source:
MTU Friedrichshafen GmbH
Turbocharger
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Introduction
5Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Source:
MTU Friedrichshafen
GmbH
Introduction Centrifugal
CompressorTurbocharger
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Introduction
6Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Source:
MTU Friedrichshafen GmbH
Performance Map
Introduction
Centrifugal
Compressor
isolines
efficiency
Turbocharger
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Introduction
7Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Source:
MTU Friedrichshafen GmbH
Performance Map
Introduction
Centrifugal
Compressor
isolines
efficiency
Turbocharger
1. Objective: Increase Efficiency
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Introduction
8Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
full-load curve
Source:
MTU Friedrichshafen GmbH
Performance Map
Introduction
Centrifugal
Compressor
isolines
efficiency
Turbocharger
1. Objective: Increase Efficiency
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Introduction
9Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
full-load curve
Source:
MTU Friedrichshafen GmbH
Performance Map
Introduction
Centrifugal
Compressor
isolines
efficiency
Turbocharger
1. Objective: Increase Efficiency
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Introduction
10Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
full-load curve
Source:
MTU Friedrichshafen GmbH
Performance Map
Introduction
Centrifugal
Compressor
isolines
efficiency
Turbocharger
1. Objective: Increase Efficiency
2. Objective: Increase Performance Map Width
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Introduction
11Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
1. Objective: Increase Efficiency
2. Objective: Increase Performance Map Width
Problem: A pure aerodynamic optimization often leads
to a poor structural integrity.
1. Constraint: Von Mises Stresses
2. Constraint: Eigenfrequency
CFD
CSM
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Contents
12Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
Optimization-Workflow
Results
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Workflow
13Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
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Workflow - Parametrization
14Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Impeller
Diffuser
Volute
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Workflow - Parametrization
15Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
3D Camber Surfacewith variable
blade ruling
Meridional Betaangle - Distribution
Source:
Friendship Systems
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Workflow - Parametrization
16Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Thicknessdistribution
3D Blade
Source:
Friendship Systems
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Workflow - Parametrization
17Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Geometry Export:
CFD (Meridional Contour, Blades) → geomTurbo (Numeca)
CSM (Impeller Solid) → Parasolid
Solid Final 3D Impeller and Diffuser
Source:
Friendship Systems
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Workflow - Parametrization
18Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
A
AA-A
Volute
Geometry Export:
CFD → Parasolid
Source:
Friendship Systems
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Workflow - Parametrization
19Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Parametrisierung
• Hub / Shroud
• Blades
• Main- and splitterblade
With variable blade ruling and non-linear
Leading Edge
• Diffuser
With variable blade ruling and non-linear
Leading/Trailing Edge
• Impeller back
• Volute
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Workflow
20Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
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Workflow - CFD
21Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Solver Numeca FINE/Turbo
Objectives:
• Isentropic Efficiency
𝜂𝐷𝑃
• Performance Map Width𝜋ℎ𝑖𝑔ℎ𝑙𝑦 𝑡ℎ𝑟𝑜𝑡𝑡𝑙𝑒𝑑
𝜋𝐷𝑃
Constraints:
• Total Pressure Ratio
𝜋𝐷𝑃
• Choke Mass Flow
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Workflow - CSM
22Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
Von Mises Stress
Main blade
Fillet
Constraints:
• 1. blade eigenfrequency
• Max. von Mises stress:
• Main blade
• Splitter blade
• Fillet
• Bottom
• Drill
low
high Splitter
BottomCalculix
Drill
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Workflow
23Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Workflow
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Contents
24Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Introduction
Optimization-Workflow
Results
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Results
25Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Results
• Evolutionary Algorithm + RSM
• 59 Parameters
• 1313 Designs
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Results
26Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Results
Choke-Mass flow > Choke_constraint
PI > PI_constraint
baseline
selected DesignsD477
D1808
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Results
27Gas Turbines and Aerospace Propulsion | Johannes Ratz 26.09.2019
Results
𝜂𝐷𝑃 → + 2.2 percentage points
𝜋𝐷𝑃 → - 0.1 (3.25%)
Map width (ሶ𝑚𝐶ℎ𝑜𝑘𝑒− ሶ𝑚𝑆𝑡𝑎𝑙𝑙
ሶ𝑚𝐶ℎ𝑜𝑘𝑒)
→ + 5.3 percentage points
D477
𝜂𝐷𝑃 → + 1.4 percentage points
𝜋𝐷𝑃 → - 0.17 (5.5%)
Map width (ሶ𝑚𝐶ℎ𝑜𝑘𝑒− ሶ𝑚𝑆𝑡𝑎𝑙𝑙
ሶ𝑚𝐶ℎ𝑜𝑘𝑒)
→ + 5 percentage points
D1808
Compliance of
structural constraints
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The authors acknowledge the financial support
by the Federal Ministry for Economic Affairs and
Energy of Germany (BMWi) in the project
GAMMA (project number 03ET1469).
Thank You for Your Attention!