AeroFuelSystem Part1 Slides
6
8/20/2019 AeroFuelSystem Part1 Slides http://slidepdf.com/reader/full/aerofuelsystem-part1-slides 1/6 Arlie Nuetzel Application Engineer Mechanical Analysis Division November, 2015 Aerospace Fuel System Modeling with Flowmaster www.mentor.com Mentor GraphicsCorp. CompanyConfidential Agenda AN, Aerospace Fuel System Modeling 1, Nov 2015 2 Flowmaster Overview Introduction to the 1D System Model Model Detail Case Study: Ground Refueling — Initial pressure/flow distribution — Balancing flow distribution – Increasing tank restriction – Increasing refuel line size — Transient surge analysis Summary Next Time… Q&A www.mentor.com Mentor GraphicsCorp. CompanyConfidential De-risk the Engineering Process Information Risk 1 st Physical Prototype % Time Virtual Prototypes Testing Effort Physical Testing is time consuming and expensive Strong desire of companies to use Virtual Prototyping and Testing technology to examine more variants in reduced time and understand what needs to be tested and why 3 AN, Aerospace Fuel System Modeli ng 1, Nov 2015 www.mentor.com Mentor GraphicsCorp. CompanyConfidential Meeting Design Requirements Flowmaster V7 is a system level thermo-fluid CFD solution used to understand pressures, temperatures, and flow rates in complex fluid systems through the development process Built-in loss data from Internal Flow Systems by D.S. Miller Steady state and transient Liquid, gas, refrigerant & 2-phase steam Specialty solvers — Heat Transfer — Swirl — Priming — Flow Balancing 4 AN, Aerospace Fuel System Model ing 1, Nov 2015 www.mentor.com Mentor GraphicsCorp. CompanyConfidential Flowmaster - Across Many Industries We are committed to “ helping our customers make a difference ” We are committed to “ helping our customers make a difference ” Aerospace Automotive Marine Oil & Gas Power Gen Process Rail Water 5 AN, Aerospace Fuel System Modeli ng 1, Nov 2015 www.mentor.com Mentor GraphicsCorp. CompanyConfidential 1D AIRCRAFT FUEL SYSTEM MODEL
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Transcript of AeroFuelSystem Part1 Slides
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 16
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983089
Arlie Nuetzel
Application Engineer
Mechanical Analysis Division
November 2015
Aerospace Fuel System
Modeling withFlowmaster
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Agenda
AN Aerospace Fuel System Modeling 1 Nov 20152
Flowmaster Overview
Introduction to the 1D System Model
Model Detail
Case Study Ground Refueling mdash Initial pressureflow distribution mdash Balancing flow distribution
ndash Increasing tank restriction ndash Increasing refuel line size
mdash Transient surge analysis
Summary
Next Timehellip
QampA
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
De-risk the Engineering Process
Information Risk 1st PhysicalPrototype
Time
VirtualPrototypes
Testing Effort
Physical Testing is time
consuming and
expensive
Strong desire of
companies to use
Virtual Prototypingand
Testing technology to
examine more variants in
reduced time and
understand what needs
to be tested and why
3 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Meeting Design Requirements
Flowmaster V7 is a system level thermo-fluid CFD solution used to
understand pressures temperatures and flow rates in complex
fluid systems through the development process
Built-in loss data from Internal FlowSystems by DS Miller
Steady state and transient
Liquid gas refrigerant amp 2-phasesteam
Specialty solvers mdash Heat Transfer mdash Swirl mdash Priming mdash Flow Balancing
4 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Flowmaster - Across Many Industries
We are committed to ldquo helping our customers make a difference rdquo We are committed to ldquo helping our customers make a difference rdquo
Aerospace
Automotive
Marine
Oil amp Gas
Power Gen
Process
Rail
Water
5 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
1D AIRCRAFT FUEL SYSTEM
MODEL
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 26
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983090
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Fuel System Model
7
APUREFUEL COUPLING REFUEL COUPLING
CENTER RIGHT MAINLEFT MAIN
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Flowmaster Model Detail
8
Engine
mdash Modeled as flow sink Engine FeedCrossfeed Piping
Fuel Pumps mdash Rotodynamic w check valve mdash Parallelredundant operation
Fuel Tank mdash Single three-armed tank
Tank TransferRefuel mdash Valve mdash Filter loss mdash Transferrefuel piping
Refuel Coupling mdash Modeled as flow source
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Flowmaster Model Detail
9
Engine FeedCrossfeed Piping mdash Left center right isolation valves mdash Transfer piping with valve
Fuel Pumps mdash Rotodynamic w check valve mdash Parallelredundant operation
Fuel Tank mdash Single three-armed tank
TransferRefuel Piping
Refuel mdash Valve mdash Filter loss
APU mdash Modeled as flow sink
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
CASE STUDY
GROUND REFUELING
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Ground Refueling
11
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate valve closure induced surge
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Ground Refueling ndash Steady State
12
Baseline Analysis
Left Side Refuel Port ndash 500 GPM
All Tank Valves Open
EnginesAPU Off
Pumps Off
AN Aerospace Fuel System Modeling 1 Nov 2015
500 GPM
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 36
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983091
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Volumetric Flow Rate Results
13 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Absolute Total Pressure Results
14 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure Drop Results
15 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Unbalanced Flow
16
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control
mdash Combination
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control mdash Combination
Problem Unbalanced Flow
17
50
50
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction Pressure Drop Results
18 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 46
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983092
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction FlowPressure Results
19 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem
mdash Single side refueling leads to ndash Large pressure difference ndash Imbalance in flow rates
Solutions mdash Flow restrictions at tanks
ndash High input pressure ndash Some imbalance remains
mdash Optimized line sizes mdash Active control mdash Combination
Problem Flow Balance
20 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study
21
Parametric Studies ndash Automated Batch Analysis ndash Manual ndash constant automatic or discrete ndash Latin square ndash Monte Carlo
mdash Pick Three ndash Start point ndash End point ndash Increment ndash Number of values
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study - Results
22
Parametric Results
ExcelXML Exportable
FMU Compatible
Flow rates trend together as pipe size increases
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Steady State Ground Refueling
23
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate any valve closure induced surge
45rdquo
2908 psia
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure SurgeWater Hammer mdash Rapid valve closures mdash Control valve lsquohuntingrsquo mdash Pump speed changes
mdash Described by the Joukowsky equation
ndash
983101
ndash where is wave speed
ndash Bulk modulus of the fluid ndash Density ndash Modulus of elasticity of pipe ndash Diameter ndash Wall thickness ndash Restraint
mdash Solved with mesh method of characteristics approach ndash Elastic pipes
Problem Transient SurgeHammer
24 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 56
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983093
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
25
Scenario
mdash Fueling from left at high rate mdash Sudden valve closure of right tank inlet valve
Investigate mdash Surge pressure mdash Attenuation from tanks friction mdash Cavitation
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
26
Pressure boundary condition (2908 psia) based on 500
GPM flow from previous study Leftcenter tanks closed
Tabular valve controller ndash 01 sec closure
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
27 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient SurgeHammer ndash Resolution
28
Pressure boundary condition (2908 psia) based on 500GPM flow from previous study
Tabular valve controller ndash 025 sec ndash 1 sec closure
Leftcenter tanks closed v opened
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
29 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient Surge Results
30 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 26
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983090
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Fuel System Model
7
APUREFUEL COUPLING REFUEL COUPLING
CENTER RIGHT MAINLEFT MAIN
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Flowmaster Model Detail
8
Engine
mdash Modeled as flow sink Engine FeedCrossfeed Piping
Fuel Pumps mdash Rotodynamic w check valve mdash Parallelredundant operation
Fuel Tank mdash Single three-armed tank
Tank TransferRefuel mdash Valve mdash Filter loss mdash Transferrefuel piping
Refuel Coupling mdash Modeled as flow source
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Flowmaster Model Detail
9
Engine FeedCrossfeed Piping mdash Left center right isolation valves mdash Transfer piping with valve
Fuel Pumps mdash Rotodynamic w check valve mdash Parallelredundant operation
Fuel Tank mdash Single three-armed tank
TransferRefuel Piping
Refuel mdash Valve mdash Filter loss
APU mdash Modeled as flow sink
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
CASE STUDY
GROUND REFUELING
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Ground Refueling
11
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate valve closure induced surge
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Ground Refueling ndash Steady State
12
Baseline Analysis
Left Side Refuel Port ndash 500 GPM
All Tank Valves Open
EnginesAPU Off
Pumps Off
AN Aerospace Fuel System Modeling 1 Nov 2015
500 GPM
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 36
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983091
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Volumetric Flow Rate Results
13 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Absolute Total Pressure Results
14 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure Drop Results
15 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Unbalanced Flow
16
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control
mdash Combination
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control mdash Combination
Problem Unbalanced Flow
17
50
50
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction Pressure Drop Results
18 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 46
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983092
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction FlowPressure Results
19 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem
mdash Single side refueling leads to ndash Large pressure difference ndash Imbalance in flow rates
Solutions mdash Flow restrictions at tanks
ndash High input pressure ndash Some imbalance remains
mdash Optimized line sizes mdash Active control mdash Combination
Problem Flow Balance
20 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study
21
Parametric Studies ndash Automated Batch Analysis ndash Manual ndash constant automatic or discrete ndash Latin square ndash Monte Carlo
mdash Pick Three ndash Start point ndash End point ndash Increment ndash Number of values
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study - Results
22
Parametric Results
ExcelXML Exportable
FMU Compatible
Flow rates trend together as pipe size increases
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Steady State Ground Refueling
23
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate any valve closure induced surge
45rdquo
2908 psia
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure SurgeWater Hammer mdash Rapid valve closures mdash Control valve lsquohuntingrsquo mdash Pump speed changes
mdash Described by the Joukowsky equation
ndash
983101
ndash where is wave speed
ndash Bulk modulus of the fluid ndash Density ndash Modulus of elasticity of pipe ndash Diameter ndash Wall thickness ndash Restraint
mdash Solved with mesh method of characteristics approach ndash Elastic pipes
Problem Transient SurgeHammer
24 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 56
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983093
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
25
Scenario
mdash Fueling from left at high rate mdash Sudden valve closure of right tank inlet valve
Investigate mdash Surge pressure mdash Attenuation from tanks friction mdash Cavitation
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
26
Pressure boundary condition (2908 psia) based on 500
GPM flow from previous study Leftcenter tanks closed
Tabular valve controller ndash 01 sec closure
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
27 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient SurgeHammer ndash Resolution
28
Pressure boundary condition (2908 psia) based on 500GPM flow from previous study
Tabular valve controller ndash 025 sec ndash 1 sec closure
Leftcenter tanks closed v opened
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
29 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient Surge Results
30 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 36
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983091
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Volumetric Flow Rate Results
13 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Absolute Total Pressure Results
14 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure Drop Results
15 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Unbalanced Flow
16
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control
mdash Combination
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem mdash Single Side Refueling Leads To
ndash Large pressure difference ndash Imbalance in flow rates
Potential Solutions mdash Flow restrictions at tanks mdash Optimized line sizes mdash Active control mdash Combination
Problem Unbalanced Flow
17
50
50
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction Pressure Drop Results
18 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 46
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983092
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction FlowPressure Results
19 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem
mdash Single side refueling leads to ndash Large pressure difference ndash Imbalance in flow rates
Solutions mdash Flow restrictions at tanks
ndash High input pressure ndash Some imbalance remains
mdash Optimized line sizes mdash Active control mdash Combination
Problem Flow Balance
20 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study
21
Parametric Studies ndash Automated Batch Analysis ndash Manual ndash constant automatic or discrete ndash Latin square ndash Monte Carlo
mdash Pick Three ndash Start point ndash End point ndash Increment ndash Number of values
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study - Results
22
Parametric Results
ExcelXML Exportable
FMU Compatible
Flow rates trend together as pipe size increases
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Steady State Ground Refueling
23
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate any valve closure induced surge
45rdquo
2908 psia
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure SurgeWater Hammer mdash Rapid valve closures mdash Control valve lsquohuntingrsquo mdash Pump speed changes
mdash Described by the Joukowsky equation
ndash
983101
ndash where is wave speed
ndash Bulk modulus of the fluid ndash Density ndash Modulus of elasticity of pipe ndash Diameter ndash Wall thickness ndash Restraint
mdash Solved with mesh method of characteristics approach ndash Elastic pipes
Problem Transient SurgeHammer
24 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 56
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983093
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
25
Scenario
mdash Fueling from left at high rate mdash Sudden valve closure of right tank inlet valve
Investigate mdash Surge pressure mdash Attenuation from tanks friction mdash Cavitation
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
26
Pressure boundary condition (2908 psia) based on 500
GPM flow from previous study Leftcenter tanks closed
Tabular valve controller ndash 01 sec closure
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
27 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient SurgeHammer ndash Resolution
28
Pressure boundary condition (2908 psia) based on 500GPM flow from previous study
Tabular valve controller ndash 025 sec ndash 1 sec closure
Leftcenter tanks closed v opened
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
29 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient Surge Results
30 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 46
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983092
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
High Tank Restriction FlowPressure Results
19 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem
mdash Single side refueling leads to ndash Large pressure difference ndash Imbalance in flow rates
Solutions mdash Flow restrictions at tanks
ndash High input pressure ndash Some imbalance remains
mdash Optimized line sizes mdash Active control mdash Combination
Problem Flow Balance
20 AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study
21
Parametric Studies ndash Automated Batch Analysis ndash Manual ndash constant automatic or discrete ndash Latin square ndash Monte Carlo
mdash Pick Three ndash Start point ndash End point ndash Increment ndash Number of values
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Line Size Parametric Study - Results
22
Parametric Results
ExcelXML Exportable
FMU Compatible
Flow rates trend together as pipe size increases
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Case Study Steady State Ground Refueling
23
Simulation Goals mdash Steady State
ndash Optimize line sizelosses to balance flow if possible ndash Determine refueling pressure required for desired flow rate
mdash Transient ndash Investigate any valve closure induced surge
45rdquo
2908 psia
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Pressure SurgeWater Hammer mdash Rapid valve closures mdash Control valve lsquohuntingrsquo mdash Pump speed changes
mdash Described by the Joukowsky equation
ndash
983101
ndash where is wave speed
ndash Bulk modulus of the fluid ndash Density ndash Modulus of elasticity of pipe ndash Diameter ndash Wall thickness ndash Restraint
mdash Solved with mesh method of characteristics approach ndash Elastic pipes
Problem Transient SurgeHammer
24 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 56
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983093
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
25
Scenario
mdash Fueling from left at high rate mdash Sudden valve closure of right tank inlet valve
Investigate mdash Surge pressure mdash Attenuation from tanks friction mdash Cavitation
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
26
Pressure boundary condition (2908 psia) based on 500
GPM flow from previous study Leftcenter tanks closed
Tabular valve controller ndash 01 sec closure
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
27 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient SurgeHammer ndash Resolution
28
Pressure boundary condition (2908 psia) based on 500GPM flow from previous study
Tabular valve controller ndash 025 sec ndash 1 sec closure
Leftcenter tanks closed v opened
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
29 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient Surge Results
30 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 56
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983093
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
25
Scenario
mdash Fueling from left at high rate mdash Sudden valve closure of right tank inlet valve
Investigate mdash Surge pressure mdash Attenuation from tanks friction mdash Cavitation
AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
26
Pressure boundary condition (2908 psia) based on 500
GPM flow from previous study Leftcenter tanks closed
Tabular valve controller ndash 01 sec closure
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
27 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient SurgeHammer ndash Resolution
28
Pressure boundary condition (2908 psia) based on 500GPM flow from previous study
Tabular valve controller ndash 025 sec ndash 1 sec closure
Leftcenter tanks closed v opened
AN Aerospace Fuel System Modeling 1 Nov 2015
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Problem Transient SurgeHammer
29 AN Aerospace Fuel System Modeling 1 Nov 2015 wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Transient Surge Results
30 AN Aerospace Fuel System Modeling 1 Nov 2015
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
8202019 AeroFuelSystem Part1 Slides
httpslidepdfcomreaderfullaerofuelsystem-part1-slides 66
983117983141983150983156983151983154 983111983154983137983152983144983145983139983155 983127983141983138 983123983141983149983145983150983137983154983098
983105983141983154983151983155983152983137983139983141 983110983157983141983148 983123983161983155983156983141983149 983117983151983140983141983148983145983150983143 983159983145983156983144 983110983148983151983159983149983137983155983156983141983154 991251 983120983137983154983156 983089
983094
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Summary
31 AN Aerospace Fuel System Modeling 1 Nov 2015
Representative 1D fuel system model
Ground Refueling Scenario mdash Sizeoptimize system for single sided refueling
ndash Pipe size using parametric study ndash Restrictor size
mdash Determine system pressure mdash Transient surge analysis
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
Upcoming Topics
32 AN Aerospace Fuel System Modeling 1 Nov 2015
Episode Two
mdash Dynamic control ndash Scheduled refueling ndash In flight fuel transfer ndash Mission profiles
Episode Three mdash Advanced tank component
ndash Complex venting ndash Complex inerting
wwwmentorcom
Mentor GraphicsCorp CompanyConfidential
